B737NG Air Systems

7/26/2019 B737NG Air Systems

1/10

Air Systems

During preflight procedure the trim air switch is left in the OFF position and only one pack is

selected ON for air conditioning. What is the consequence? Since the trim air is off oth packs will a!erage the temperature that satisfies the "one

which requires the most cooling

During single pack operation the "one temperature is controlled the same as during two

pack operation.

With the #$%& A%$ selected OFF' the pack attempts to produce an air temperature tosatisfy the a!erage temperature demands of all three "ones.

%f a passenger cain "one trim air' or all trim air is lost' the forward and aft "one

temperature demands will e a!eraged for control of the left pack.

When pressing &aster (aution $ecall the (ON# (A) amer *ON+ #+&, light illuminates.

What is correct?

#his indicates a failure of oth the primary and standy temperature control systems.

Due to failure of the primary flight deck temperature control' automatic switching to the

ackup system has occurred.

#his indicates one ,A(- has o!erheated and has to e reset y pushing the trip reset

utton. #his indicates that oth temperature controllers will regulate the temperature to a preset

!alue.

When will the descent mode e acti!ated in the pressuri"ation system?

When #D is reached.

When retard is announced in the F&A.

When descending /.01psi elow the selected flight altitude.

When within 21 /// feet of the landing airport.

Due to a malfunction you are required to return to the airport of departure. #o a!oid the OFF

S(3+D D+S(+N# warning you reset the F4# A4#. What can you e5pect? #he system will e recalculating the pressuri"ation for the departure airport

#he pressuri"ation will increase its !entilation and possily pressuri"ation will e lost

#he automatic aort capaility for the departure airport is lost

Nothing will happen and you will still get the OFF S(3+D D+S(+N# warning.

From where does the (ain Auto (ontroller get its inputs.

From the static ports

From the (aptain6s (D7

From the AD%$76s

From the +F%S control panel

Where are the leed trip sensors installed?

On the 8th Stage leed air line.

On the engine side of the engine leed air !al!e.

Sensors are positioned on oth sides of the engine leed air !al!e.

On the leed air duct prior to the pack !al!e.

#he right W%N9:)OD; O


2/10

#he keel eam

A,7 leed duct

4eft aircond ay

$ight engine strut

What is the purpose of the recirculation fans?

#o increase the pressure in the cain.

#o decrease the air conditioning system pack load

%f increased smoke remo!al is required #o operate as air mi5ers in the mi5 manifold

#he wing:ody o!erheat light comes on. What is the related master caution warning?

O


3/10

A motor supplied from D( us 2.

$equires A( power from transfer us 2.

What is the primary source of conditioned air for the cockpit?

#he $ight pack.

#he 4eft pack.

)oth packs.

9round air

During descent when the descent mode is acti!ated=

Aircraft descends /.01 psi elow the selected F4# A4#.

Aircraft descends /.1/ elow the selected F4# A4#.

Aircraft descends /.01 psi elow the selected 4AND A4#@

Aircraft descends /.1/ psi elow the selected 4AND A4#.

#he ma5imum differential pressure is=

.8/ psi

.B1 psi

.C1 psi

8.2/ psi

What are the causes of an Amer A7#O FA%4 light?

4oss of D( power@

+5cessi!e rate of cain press change or cain altitude ao!e 21// ft@

)oth ao!e statements are correct@

9i!en the scenario that the e5pected cruise le!el of F4>2/ was selected into the F4# A4#

selector during preflight' ut susequently the A( climed to F4>8/' would you e5pect=

A differential pressure of .B1 psi maintained y the negati!e pressure relief !al!e@

A differential pressure of 8.2 psi maintained y the positi!e pressure relief !al!e@

A differential pressure of .>1 psi maintained y the forward outflow !al!e@

#he cain will automatically pressuri"e to /.201 ,S%D on the ground when=

+ngine thrust is increased towards takeoff thrust.

When the ,S+7 is acti!ated.

When the aircraft goes into the ground mode of the airground sensor.

A7#O mode acti!e. #he A7#O FA%4 light illuminates when=

#he cain altitude e5ceeds 21'//ft.

#he rate of cain pressure change e5ceeds 2/// ftmin.

#he pressuri"ation controller is mo!ed to A4#N.

When oth the A7#O FA%4 light and the A4#N light illuminate=

,ressuri"ation has automatically switched to the A4#N system.

,ressuri"ation has automatically switched to the &AN system.

,ressuri"ation has automatically switched to the opposite automatic controller.

Where do the A7#O mode controllers recei!e their arometric information from?

#he captains pitotstatic system.
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4/10

#he FOs pitotstatic system.

#he AD%$7s.

4oss of airflow due to failure of an equipment cooling fan results in illumination of the related

equipment cooling OFF light. Selecting the alternate fan should restore airflow and e5tinguish the

OFF light within appro5imately EEEEE.

1 seconds

>/ seconds

2 minute

> minutes

Where is the forward outflow !al!e located?

ust in front of the forward airstairs.

Forward of the left hand air conditioning inlet.

#here is no forward outflow !al!e.

#he forward outflow !al!e=

(loses automatically to assist in maintaining cain pressure when the main outflow !al!e

is almost closed or the recirculation fan is operating.

%s motor operated and operates independently of the main outflow !al!e. Opens while on the ground and in flight with less than 0.1 psig cain differential pressure.

has een remo!ed from the >:C//// models.

Why should li!estock GanimalsH e transported in the FWD cargo holds?

)ecause they are cooled y air from the +I+ ay.

)ecause they are heated y air from the +I+ ay.

#he FWD cargo hold is the preferred hold' ecause the door is larger than the aft cargo

door making loading easier

%f a flight is aorted' and a return to the field of departure is made' the crew=

Should reset the 4AND A4# selector to field +4+


5/10

A continuous warning horn accompanied y a &aster (aution warning.

On hearing the Altitude Warning 3orn the pilotJs first action should e to=

Analyse the situation and decide on correcti!e action.

#o don o5ygen masks.

%nitiate an emergency descent.

(ancel the Altitude Warning 3orn and call for the appropriate K$3 checklist.

An amer A7#OFA%4 indication will illuminate if one or more of the followingconditionsoccur=

A single controller failure when JA4#NJ light is also illuminated.

4oss of A( power for more than 21 seconds@ &ain Outflow !al!e D( motor fails or if the

cain altitude e5ceeds 2>'1 ft.

(ain Altitude e5ceeds 2>'1 ft@ pressurisation differential e5ceeds .C1psi or with the

loss of A( power.

(ain Altitude e5ceeds 2/'/// ft.

A decompression of the cain will result in the following=

An Altitude Warning 3orn at 2/'/// ft. At 2B'/// ft Gappro5imatelyH a J&aster (autionJ'

plus an JO!erheadJ indication on the lightglare shield will illuminate. #he o!erhead panelwill illuminate with J,AL OL; ONJ amer indications.

An Altitude Warning 3orn at 2B'/// ft. #he o!erhead panel will illuminate JA7#OFA%4J

and JA4#NJ amer indications on the pressurisation panel. #hese indications may e reset

y selecting manual mode on the pressurisation selector.

An Altitude Warning 3orn at 2/'/// ft. At 2B'/// ft the ,assenger O5ygen mask will

deploy. #o acti!ate O5ygen flow to the ,assengers the (rew must select the J,assenger

O5ygen SwitchJ to ON.

An altitude warning u""er at 2/'/// ft. At 2B'/// ft the o5ygen masks will deploy and

the o!erhead panel will show J($+W OL; ONJ.

A flight deck *ON+ #+&, light which remains illuminated after the master caution system isreset indicates=

A flight deck duct o!erheat.

A failure of the standy or primary flight deck "one controller.

)oth ao!e statements are correct.

%nsufficient trim air a!ailale from the cooling packs.

A *ON+ #+&, light may e reset y the trip reset switch on the )leed ,anel.

#rue.

False. #his reset switch is only for ,A(- and )4++D #$%, OFF resets.

False. #his reset is only for resetting a ,A(- trip.

False. #his reset switch is for )4++D #$%, OFF only.

%n (ruise the air conditioning ram air doors are=

Fully open.

Fully closed.

&odulate etween open and closed as required for pack temperature control.

&odulate as a function of airspeed.
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6/10

%f a ,A(- light can e reset y the #$%, $+S+# switch then=

#he fault was caused y an o!erheat trip.

#he fault was caused y a controller fault.

#he fault was caused y an o!erheat trip or y a controller fault.

#he pack should e selected off as per the K$3.

#he ram air system pro!ides cooling air for= #he cargo area.

#he heat e5changers. #he ++.

Deflector doors are installed forward of the ram air inlet doors to pre!ent slush ingestion priorto liftoff and after touchdown. Deflector doors e5tend when acti!ated=

+lectrically y the air:ground safety sensor

3ydraulically when e5tended the main landing gear

+lectrically Gsame switch as the recirculation fansH.

%f all "one controls and primary pack controls fail' the standy pack controlscommand thepacks to produce air temperatures which will satisfy the a!eragetemperature demand of the two

cain "ones. #he trim air modulating !al!es will= Open.

(lose.

%f all #emperature Selectors are positioned OFF' the pack controls will cause the 4eft pack to

maintain a fi5ed temperature of EEEE and the $ight pack to maintain EEEE as measured at the pack

temperature sensor.

0/M( GCMFH and 2M( GC1MFH

0BM( G1MFH and 2M( GC1MFH

2M( GC1MFH and 00M( G0MFH

O!erheat detection is pro!ided y temperature sensors located= %n the mi5 manifold.

Downstream of the packs.

Downstream of the packs and the mi5 manifold.

Downstream of the packs' the trim air !al!e and the mi5 manifold.

#he recirculation fan system circulates air from the passenger cain around thelining of the

forward cargo compartment. When the o!eroard e5haust !al!e isclosed' e5haust air from theequipment cooling system is also diffused to the lining of the aft cargo compartment for additional

inflight heating.

#rue

False

Forward cargo compartment only

#he cain pressure controller controls cain pressure in the following modes= A7#O

GautomaticH : A4# GalternateH : &AN GmanualH.

All three modes use D( motor.

Automatic mode uses A( motor while the two other modes use D( motor.
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7/10

Automatic and alternate modes use A( motor while the manual mode use D( motor.

(ain altitude is normally rate:controlled y the cain pressure controller up to a cain altitude

of EEEE feet at the airplane ma5imum certified ceiling of EEEEfeet.

2/ /// ft and B2 /// ft.

/// ft and B2 /// ft.

20 /// ft and B2 /// ft.

1// ft and B2 /// ft.

#he air data inertial reference units GAD%$7sH pro!ides amient static pressure'aro corrected

altitude' non corrected altitude and calirated airspeed to othautomatic controllers. #he AD%$7srecei!e arometric corrections from the(aptainJs and First OfficerJs )A$O reference

selectors.#he automatic controllers also recei!e=

#hrottle position from oth stall management computers.

#hrottle position from oth stall management computers and signals from the airground

sensors.

#hrottle position from oth stall management computers and signals from the %$S.

(ain air outflow is controlled y the outflow !al!e and the o!eroard e5haust!al!e. A small

amount is also e5hausted through toilet and galley !ents'miscellaneous fi5ed !ents' and y sealleakage.

#rue

False

%f oth the primary and the standy pack controls fail for the same pack' the,A(-' &AS#+$

(A7#%ON' and A%$ (OND System Annunciator lightsilluminate.

#he pack will continue to operate without control unless e5cessi!e

#he affected pack is controlled y the JmainJ standy pack control

#he pack will e inoperati!e

&anual &ode Operation= a separate D( motor' powered y the D( standy system' dri!es theoutflow !al!e at a slower rate than the automatic modes. Outflow !al!e full range of motion takes

up to 0 minutes.

#rue

False

Fortunately Outflow !al!e full range of motion takes up to 0/ seconds only.

A D7(# O


8/10

+ngine starting' air conditioning' pressuri"ation' wing I engine anti:ice' hydraulic

reser!oirs and water tank pressuri"ation.

+ngine leed air is otained from=

Bth and 8th stage of the compressor section.

1th and 8th stage of the compressor section.

Bth and th stage of the compressor section.

1th and th stage of the compressor section.

%llumination of the amer )4++D #$%, OFF light indicates what !al!e has automatically

closed?

&odulating and Shutoff !al!e.

+ngine )leed Air !al!e.

%solation !al!e.

1th !al!e of the compressor section.

3ow are the +ngine )leed Air !al!es powered?

#hey are A( acti!ated and pneumatically operated.

#hey are D( acti!ated and pneumatically operated.

#hey are pneumatically acti!ated and A( operated. #hey are pneumatically acti!ated and D( operated.

An illuminated )4++D #$%, OFF light indicates=

#oo high temperature in leed air duct and leed air !al!e stays open.

#oo high temperature in leed air duct and leed air !al!e stays closes.

#oo high pressure in leed air duct and leed air !al!e stays open.

#oo high temperature or pressure in leed air duct and leed air !al!e stays closes.

What is the position of the isolation !al!e when the %SO4A#%ON


9/10

%n the ,A(- #$%, OFF Non Normal (heck:4ist' the crew selects a warmer temperature inorder to=

$educe cain airflow.

$educe the workload on the other pack.

$educe the workload on the affected air conditioning pack

$educe the air flow through the air mi5 !al!es.

#he amer D7A4 )4++D 4ight is illuminated efore starting engines. What should you do?

Nothing. #his is normal condition efore engine start.

Do not start the engines' call &aintenance.

Do not start the engines' check &+4.

Shut down the A,7 and use a pneumatic ground cart for engine start.

#he motori"ed +5haust !al!e=

Allows for increased !entilation in the smoke remo!al configuration.

Ser!es as ackup to the outflow !al!e if the outflow !al!e fails.

%s normally open in pressuri"ed flights ao!e '/// feet.

All the ao!e.

#he amer D7A4 )4++D light indicates apossile A,7 ack pressure condition and thrustmust e limited to %D4+.

#rue.

False.

What happens to engine fan air that is used to cool engine leed air?

%t is ducted into the pneumatic manifold.

%t is ducted into the crossleed manifold.

%t is discharged o!eroard.

%t is ducted into the 1th stage compressor section.

What causes the amer ,A(- #$%, OFF 4ight to illuminate? &ain distriution duct temperature has e5ceeded limits.

(ompressor outlet duct temperature has e5ceeded limits

#urine inlet duct temperature has e5ceeded limits.

All of the ao!e.

#he ram air system deflector doors=

Are always e5tended when the gear is down.

+5tend during slow flight when flaps are not retracted.

&odulate etween fully e5tended and retracted through the entire flight.

+5tend on the ground only.

%f any indi!idual "one is switched OFF' the #emperature Selector setting will e ignored y the

temperature control system.

#rue

False
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10/10

#he +quipment (ooling Supply or +5haust OFF light illuminated indicates a loss of airflowfrom the selected cooling fan. ;ou position the +K7%,&+N# (OO4%N9 S7,,4;+L3A7S#

switch on A4#+$NA#+

No further action is necessary in flight if the equipment cooling OFF light does not

e5tinguish.

Di!ersion is necessary in flight if the equipment cooling OFF light does not e5tinguish.

Descending elow F401/ is necessary in flight if the equipment cooling OFF light does

not e5tinguish.

Descending elow F40// is necessary in flight if the equipment cooling OFF light does

not e5tinguish.

See K$3 Air Systems : +K7%,&+N# (OO4%N9 OFF

A leak in the A,7 )leed Air Duct will e indicated y=

$ight W%N9)OD; O

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B737NG Air Systems