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Air Conditioning and Cabin Pressurization Maximum differential pressure (relief valves) Maximum negative differential pressure 8.6 psi -1.0 psi Note: The values above approximate the pressure at which the safety valves will open. The use of external high pressure air to operate the packs on the ground is acceptable, provided the equipment is owned or controlled by Delta Air Lines. When the OAT is above 120?F, do not power the avionics for more than two hours unless the avionics ventilation system is operating normally Engine anti-ice must be ON during all ground and flight operations when icing conditions exist or are anticipated, except during climb and cruise when the temperature is below -40. C SAT Note: Do not rely on airframe visual cues to turn engine anti-ice on. Engine anti-ice must be on prior to and during descent in icing conditions, including temperatures below -40. Wing anti-ice may be used to o either prevent ice formation or to remove ice accumulations from the wing leading edges. The flight crew should turn wing anti-ice ON whenever there is an indication the airframe is accumulating ice. The indication may be observed be observed on the visual ice indicator between the windshields or on the wipers. Avoid extended flight in icing conditions with the slats extended. Non-ILS Approaches The use of the autopilot and flight director with the LOC pb is approved for localizer and LDA without glideslope approaches. The use of the autopilot and flight director in FINAL APP mode is approved for RNAV (GPS), VOR, and NDB approaches. Note: Raw data from the specified approach navaid must be displayed on the PFD or ND and monitored during all approaches. DAL does not require demonstrated proficiency for hand flown non-ILS approaches in the Airbus. Autolands are not permitted at Anchorage (PANC) or Fairbanks (PAFA) with aircraft 3209-3270 due to ADIRS magnetic variation tables. All CAT II and CAT III approaches must terminate with an autoland or missed approach.

Report this Document Download Now Save Save Delta A320 OM Vol1.pdf For Later 0 ratings 0% found this document useful (0 votes) 155 views 472 pages Delta A320 OM Vol1.pdf Uploaded by Anthony Geino Description: Full description Save Save Delta A320 OM Vol1.pdf For Later 0% 0% found this document useful, Mark this document as useful 0% 0% found this document not useful, Mark this document as not useful Embed Share Print Download Now Jump to Page You are on page 1 of 472 Search inside document Browse Books Site Directory Site Language: English Change Language English Change Language. Something went wrong. View cart for details. Cartes Pokemon neuves GX ESCOUADE brillantes en francais.User Agreement, Privacy, Cookies and AdChoice Norton Secured - powered by Verisign Amounts shown in italicized text are for items listed in currency other than Canadian dollars and are approximate conversions to Canadian dollars based upon Bloomberg's conversion rates. For more recent exchange rates, please use the Universal Currency Converter This page was last updated: 16-Sep 08:52. Number of bids and bid amounts may be slightly out of date. See each listing for international shipping options and costs. It looks like your browser needs updating. For the best experience on Quizlet, please update your browser. Learn More. Note: Do not exceed Delta limit speeds for flap extension (except as directed by a non-normal procedure or during flap retraction). At high gross weights, use the higher of either VFE - 10 or lowest allowable speed for the configuration. The landing gear tires are limited to a ground speed of 195 kts The maximum speed with the flight deck window open is 200 kts The maximum speed for operating windshield wipers is 230 kts. With passengers on board, the escape slides must be armed (verified on ECAM) before moving the aircraft away from the gate and must remain armed until the aircraft returns to the gate.

Status of the aft cargo heat system can be monitored by referencing the COND or CRUISE pages. There are two pressurization controllers installed. However only one is active at a time. The active controller can be viewed on the CAB PRESS page as a SYS 1 or SYS 2 labeled in green. Automatic: 1. The active and standby controllers transfer roles shortly after landing. 2. The standby controller will become active in the event the active controller fails. Manual: 3. The standby and active controllers can be transferred manually by placing the MODE SEL pb to MAN for 10 seconds, and then returning it back to the AUTO (lights out) mode. In AUTO, the FMGCs provide the landing field elevation so threat the pressurization controllers can construct and optimized pressure schedule. Outside of the AUTO detent, the landing field elevation is set manually by referencing the scale around the selector. This is performed if: - the FMGCs are inoperative, or - the airport of intended landing is not in the FMS database. MODE SEL pb - selecting to MAN enable manual control of the outflow valve. Below a predetermined altitude no action is required. The pressurization system's abort mode automatically returns the cabin altitude to the departure airport elevation. Placing the DITCHING pb to ON causes opening below the fltation line to close. Used if warm ambient conditions exist while the aircraft is on the ground. Outside air is drawn through the open inlet valve by the blower fan where it then passes around the avionics equipment. The extract fan then pulls the heated air and expels it out through the fully open extract valve. Avionics compartment air does not pass through the aircraft skin heat exchanger or the cargo under floor. Used during flight or during cold ambient conditions on the ground. Avionics compartment air is cooled via an aircraft skin heat exchanger and circulated by the blower and extract fans. The inlet and extract valves remain closed.

Air is expelled through the cargo under floor and out through the outflow valve. Used if warm ambient conditions exist during flight. (airborne or thrust levers placed to a takeoff position while on the ground). Same as the closed configuration, except that a small internal flap withing the extract valve opens to expel some of the heated avionics compartment air overboard. Used to response to the Avionics Equipment Ventilation Computer (AVEC) sensing smoke in the avionics compartment. The BLOWER and EXTRACT pbs are placed to the OVRD position in accordance with ECAM procedure. This closes the inlet valve, stops the blower fan, and isolates the cargo under floor and aircraft skin heat exchanger. Conditioned air is provided by the air conditioning system through an air conditioning inlet valve. The extract fan draws the conditioned air through the avionics compartment.Wings - Outboard three slats (slats 3,4,and 5) Engines - Engine nacelle leading edge. Turn on wing anti-ice whenever there is an indication the airframe is accumulating ice. Indications may be observed on the visual ice indicator between the windshields or on the wipers. Engine anti-ice should be used whenever icing conditions exist or are anticipated for both ground and flight operations. Engine icing conditions exist when the OAT is 10 C or below, and visible moisture in any form is present (clouds, fog with visibility of one mile or less, rain, snow, sleet, and ice crystals). Extended flight in icing conditions should be avoided due to reduced wing anti-ice capability with the slats extended. The FACs provide flight envelope calculations to the autoflight system to ensure limits are not exceeded, such as: Maximum and minimum airspeeds Maneuvering speeds Configuration limits Alpha (angle of attack) limits. The primary tool to monitor the status and performance of the autoflight systems. Monitor the approach capabilities of the aircraft. Column 1: autothrust system indications.

The maximum continuous load for each generator is 90 KVA (100% of rated capacity). The maximum continuous load for each TR is 200 amps. Do not reset a tripped circuit breaker in flight. These may limit the N1 to a value lower than the one given above. Engine Oil System: Minimum oil quantity (ECAM indicating) before engine Start Note: At idle, oil quantity indications can decrease as much as 6 quarts. Backing the airplane with use of reverse thrust is. The Maximum APU N speed is 107% Air bleed extraction for wing anti-ice from the apu is not permitted. North 60? South not permitted. Do not operate the weather radar in a hangar or within 50 feet of any personnel or fuel spill. As a reference only, with a specific gravity of 6.676 pounds per gallon, the usable fuel with full tanks would be approximately 42,072 pounds (27,525 pounds in the wings and 14,547 in the center tank).In this case ensure the fuel temperature remains at least 3? C above the actual freeze point. The normal hydraulic operating pressure is 3,000 plus or minus 200 PSI. The terrain display is only intended as a situational awareness tool, and may not provide the accuracy on which to solely base terrain avoidance maneuvers. The theoretical minimum pavement width required: - A319 is approximately 68feet. - A320 is approximately 75feet. A 180 degree turn should not be attempted on a 75 feet wide taxiway but can be made comfortably on a 100 foot wide taxiway. The wingtip swings the largest arc during a turn, followed by tail, then the nose. Wingtip determines minimum obstruction path. They can be opened from the exterior. Overwing exits: All can be opened from the exterior. -A320: 4 overwing exits, 2 on each side. -A319: 2 overwing exits, 1 on each side Flight deck sliding windows - Cannot be opened from the outside. All normal means of door operation from the cabin are inhibited for 15 minutes. For Overwing exits - - Green Door - The door is closed and locked and the handle cover is stowed.

- Solid Amber with amber EMER EXIT the handle cover has been removed or the exit has been opened. MASK MAN ON pb - - Auto - a signal is automatically sent to open pass mask doors when cab alt exceeds 14,000 feet. - Selected - manually deploys pass masks. PASSENGER SYS ON light - illuminates white when either auto or manual signal has been sent to deploy pass masks. CREW SUPPLY pb - - controls the crew oxygen low pressure supply valve. ON - Lights out - the supply valve is open supplying low pressure oxygen to the masks. OFF - White - the supply valve is closed. OXY - senses high pressure oxygen and the indications turns amber if: - there is insufficient bottle pressure. - the CREW SUPPLY pb has been selected off. REGUL LO PR - senses low pressure oxygen and appears if inadequate pressure is being delivered to the crew oxygen masks. Pilot must activate. SHUT - Manually closes the cross bleed valve, overriding the auto logic of the Bleed Monitoring Computers. Auto - BMC's control the opening and closing of the cross bleed valve: - the cross bleed valve opens automatically if the APU bleed valve is opened. - the cross bleed closes automatically if the APU bleed valve is closed, or if a bleed air leak is detected. The GND symbol appears whenever the aircraft is on the ground. It does not indicate the presence of external high pressure air. The IP designator represents the relative location of the IP check valves. The APU bleed valve appears on the BLEED page when the APU MASTER SW pb has been selected ON. Note: It is not possible to determine whether APU bleed air is in use solely by referencing the APU BLEED pb on the overhead panel. If the primary channel fails, ALTN Mode appears in green at the top of the COND page. Automatically controlling and monitoring each pack and regulating cold air output in accordance with the demands required by the Zone Regulator. The aft compartment using the controls located on the overhead CARGO HEAT panel.

Column 2: autoflight vertical mode indications. Column 3: autoflight lateral mode indications. Column 4: approach capabilities and minimums. Column 5: Autoflight status. Green - engaged modes. Blue - armed modes of numbers. Magenta - altitude constraints ( if vertical path includes a level segment) White - approach capabilities, certain autothrust modes, and autoflight system status. Red - significant flight control system degradation. Engagement - selecting either the AP1 or AP2 pbs located on the Flight Control Unit (FCU). Disengagement: - selecting the autopilot disconnect pb on either sidestick (preferred method) - Selecting the illuminated AP1 or AP2 pb on the FCU. - Displacing either sidestick or displacing the rudder pedals. If FMGC 1 has failed, 2FD2 will be displayed. If FMGC has failed, 1FD1 will be displayed. OFF - thrust must be controlled manually using the thrust levers. - FMA coumn 1 and the bottom row of Column 5 will be blank. ARMED - Thrust output corresponds to the position of the thrust levers. -The autothrust system automatically arms if the flight directors are on and: - the thrust levers are placed to either the TOGA stop or the FLX detent during takeoff. - during flight, the aircraft is configured in FLAPS1 or greater, and the thrust levers are placed to the TOGA stop. FMA Column 1 will display a manual thrust setting (eg. Fixed - anything other than SPEED or MACH (e.g. THR CLB, THR IDLE, MAN TOGA, etc.). Variable - either SPEED or MACH, depending on aircraft altitude.A white box appears around the indication that has changed. The box only appears for a short time and then disappears. NOTE: MANAGED vertical performance (CLB or DES) requires MANAGED navigation (NAV). Pushed - commands a vertical speed of zero and aircraft levels off. NOTE: when both lateral and vertical guidance modes are engaged on a non-ILS approach, Columns 2 and 3 of the FMA combine to display FINAL APP.

Allows tuning of communication radios and standby tuning of navigation radios. ATTND ADV pb - NOT used in company procedures. In this case, the ALTN light in the pb will not illuminate. AC Buses 1 and 2 can only be powered by their respective engine generator. The spinning RAT pressurizes a Blue hydraulic pump, which in turn powers the emergency generator. NOTE: Selecting the RAT MAN ON pb on the overhead HYD panel will deploy the RAT but will not connect the emergency generator to the electrical system. The MAINT BUS switch is located on an electrical panel near the ceiling of the forward galley area. Contact maintenance. Lights out - the APU computer is deactivated, and the APU shuts down. FAULT - an automatic shutdown or failed start has occurred. NOTE: EGT protection is not provided during inflight engine starts. An active engine start sequence is occurring. When the start sequence is complete, it disappears.The CARGO SMOKE system is controlled by a two channel computer called the Smoke Detection Control Unit, or SDCU. The test occurs twice because each channel of the SDCU is being tested. The CRUISE or COND pages on the SD. NOTE: Because the cargo smoke detectors sense particulates and the discharge of halon in the affected compartment will introduce more particulates, the smoke indications will remain. The CRUISE and COND pages display Fahrenheit temperatures inside the aft compartment. Since the detectors sense particulates, de-icing fumes or exhaust from nearby external power equipment or taxiing aircraft may trigger false warnings. NOTE: On the ground, consider investigating the source of the CARGO SMOKE warning before discharging the agent.Both roll characteristics are available in Normal Law only. Bank angle hold - if the sidestick is neutralized at bank angles ?33o, a zero roll rate is commanded and the bank angle does not change; the bank angle is held.Unlike high speed and alpha protections, the pilot can override stabilities.

The aircraft will continue to decelerate and could stall. NOTE: Since there is no mechanical connection to the sidesticks, they will be inoperative. It will not degrade to Direct Law once the landing gear is extended. The sidestick priority system allows either pilot's sidestick to have sole control of the aircraft in the event of a sidestick failure, autopilot failure, or a desire to override the inputs of the opposite sidestick. The ELACs will process the sum of their inputs, up to a maximum of one sidestick's full deflection. It specifically shows the angle of the THS for nose UP or nose DN trimming. NOTE: This autopilot limitation does not apply to the A319, on which the speed brakes will respond to all lever positions. However, A319 speed brake authority in the FULL position is approximately half of that on the A320. ADIRU 1 supplies information to the CA's PFD and ND. ADIRU 2 supplies information to the FO's PFD and ND. ADIRU 3 serves as a backup. The PFD takes priority over the ND. If the outer DU is turned off or fails, the PFD automatically transfers to the inner DU. NOTE: Either FWC can perform all of the above functions. A failure of one FWC has little impact on aircraft operation.Steady - the respective ADIRU is operating normally in the align mode.Pressure reducers in the wing tank fuel pumps allow center tank fuel to have priority in the system. When one of the wing tank inner cell fuel levels reaches approximately 1,650 lbs. During engine start.In flight, the pump operates provided AC power is available, regardless of the status of the engines. Instead, it's meant to serve as a locator to assist the crew in finding the correct pb in response to reservoir malfunction procedures. In this case, the pilot must use the RAT MAN ON pb. Indicate that the gear is not locked in the selected position (e.g. gear handle down but gear not locked down). They also appear after touchdown when antiskid is active.

LO - sends progressive pressure to the brakes 4 seconds after the ground spoilers deploy. MED - sends progressive pressure to the brakes 2 seconds after the ground spoilers deploy. The aircraft is approaching the selected rate of deceleration. The terrain category still functions. NOTE: Terrain data takes priority over weather radar returns. The outer ND control knob varies brightness for both terrain and weather returns.Preventative - keep the aircraft vertical speed out of the red-shaded area on the PFD vertical speed indicator. Corrective - adjust aircraft vertical speed to stay in the green-shaded area and out of the red-shaded area. AUTO - Other and Proximate traffic is only displayed if TA or RA intruder aircraft are present. ON - Other and Proximate traffic, if present, are displayed at all times. NOTE 1: The windshear system is a reactive system only. How many SXMK's and describe. How many medical pouches and describe. How many AED's and describe. How many first aid kits and describe. How many Portable O2's and describe 5 How many Crew life vests and describe. How many Pax life vests and describe. How many Halon ext and describe 3 Range of 10 feet How many H2O water extinguishers and describe Range of 25 feet, 8 to 25 seconds of use How many PBE's and describe. How may Lav smoke detectors and describe. How many rafts and describe.Recall the AUTO (lights out) function of the BLUE ELEC PUMP pb on the overhead HYD panel. Recall what causes the FAULT light to illuminate within the PTU pb. Describe the functions of the X BLEED knob located on the overhead AIR COND panel. SHUT - ? AUTO - ? OPEN - ? SHUT - manually closes the crossbleed valve, overriding the auto logic of the Bleed Monitoring Computers (BMCs). Recall what the green GND symbol represents on the BLEED page The green GND symbol appears whenever the aircraft is on the ground. Recall the indications when external high pressure air is connected to the aircraft.

Recall when the APU bleed valve appears on the BLEED page. NOTE: It is not possible to determine whether APU bleed air is in use solely by referencing the APU BLEED pb on the overhead panel.Describe three ways for the active and standby pressurization controllers to transfer roles. Describe the function of the LDG ELEV selector on the overhead CABIN PRESS panel. In AUTO, the FMGCs provide the landing field elevation so that the pressurization controllers can construct an optimized pressure schedule. Below a predetermined altitude, no action is required. The pressurization system's abort mode automatically returns the cabin altitude to the departure airport elevation Describe the function of the DITCHING pb on the overhead CABIN PRESS panel Placing the DITCHING pb to ON causes openings below the flotation line to close. The wingtip swings the largest arc during a turn, followed by the tail, then the nose. Therefore, the wingtip determines the minimum obstruction path. Describe the location of all cabin entrance doors and emergency exits, and whether or not they can be opened from the exterior Cabin entrance doors: Both the A320 and A319 have 4 cabin entrance doors (2 on each side of the aircraft), defined as 1L, 1R, 2L, and 2R. Flight deck sliding windows: Both the A320 and A319 have sliding windows in the flight deck that may be used for emergency egress. These windows cannot be opened from the exterior Recall what occurs if the COCKPIT DOOR selector switch is momentarily placed in the LOCK position. Recall the flight deck indications when the cabin slides are armed. There are a total of 5 portable oxygen bottles stored on the aircraft Explain the controls and indicators on the overhead OXYGEN panel. PASSENGER SYS ON light - illuminates white when either an automatic or manual signal has been sent to deploy the passenger masks. NOTE: In order to provide illumination, these lights must be selected on by the pilot.