sing single le fail failur ur
ca
norm normal al law. law. Howeve However, r, multip multiple le fail failur ures es offl offlig ight ht cont contro rol, l, hydr hydrau auli lic, c, or elec electr tric ical al ys degr degrad adat atio io of'the of'the flig flight ht cont contro ro norr norrna na law, law, Th leve leve of degr degrad adat atio io will will de en th se erit erit of the failur failures. es. Degr Degrad adat atio io efth efth flig flig cont contro ro or al laws laws is some someti time me refe referr rred ed to as reco reconf nfig igur urat atio ion. n. We will stud stud thes thes reco reconf nfig igur urat atio io laws laws in orde orde of incr increa easin sin severity.
sing single le fail failur ur
ca
norm normal al law. law. Howeve However, r, multip multiple le fail failur ures es offl offlig ight ht cont contro rol, l, hydr hydrau auli lic, c, or elec electr tric ical al ys degr degrad adat atio io of'the of'the flig flight ht cont contro ro norr norrna na law, law, Th leve leve of degr degrad adat atio io will will de en th se erit erit of the failur failures. es. Degr Degrad adat atio io efth efth flig flig cont contro ro or al laws laws is some someti time me refe referr rred ed to as reco reconf nfig igur urat atio ion. n. We will stud stud thes thes reco reconf nfig igur urat atio io laws laws in orde orde of incr increa easin sin severity.
In alte altern rnat at
law: law:
"g
is
in
~fli ~fligh gh mode mode itch itch lo ol co tr l: ce vent ventle lena nal, l, su face face efle eflect ctio io deflection, ol sens sensit itiv ivit it is pr po tion tional al to ai spee spee feel feel more more sens sensit itiv ive. e. •ya is damp dampin in aval avalla labl bl with with limi limite te auth author orit ity. y. land landin in
mo e:
irec irec la
when when land landin in
is prop propor orti tion on
gear gear is sele select ct
do
to side side stic stic
(dis (discu cuss ssed ed late late
Degradatio to lt rnat ALTN LA (PRO LOST). You will se this cautio
la
is indicate
by th
in etai in th abno ma
CA
cautio
pe atio
Fi TL
mo ule.
Unde alternat Ia.w,mos protection ar lost Some ar replaced by stabilities. We will continue by studying th loss of protections.
,-
. _ . _ . _ . _ . _ . _ . _. _ . _ . _ . _ . _ . _ . _ ._ . _ . _ . _ . _ . , . _ . _
. . . . . " . , , _ _ -
..."..--,-
Pitc a.ttitud protection is lost an th flight contro computers will down pitc attitu .. sh ch prot ctio li it in no ma law, re eplace amber crosses.
by
."_
...._._._
Bank ngle ro ection is lost th PF
th gree daehes
by amber crosses.
re re lace
Th load factor limitation is simila to normalla.w Sowe will go straight to he difference et ee orma an altern te lo an high spee stability.
In alte nate la th high angl of attack pr tectio is eplace by lo spee st bility
re lace in ca
by
ctio stal wa ning spee
VSW)
As spee approaches VS in preven furthe spee loss side stick.
gentle progressiv lo
os
triggered. The aircraft will stal if th warnin Alph floo prot ctio
is igno ed
is inoper tive in lt rnat
la
In alternat
la.w,high spee stabilit
replaces high spee protection sh
,a an preven furthe spee lncrease
is
is
As in orma lew, ifVM IM is xc ed th over spee arning is trigge ed
ot ha acco ding to th failures an alternat la.wwithou stabilit ca exist. Inthis case stabilitie StaUa operative.
•-=0
.
"
•
.
'-·"""'·""''';::::;'.r
__.
.,_,._
nl th lo
fact
ar lost over spee
arning
lo
limita io
ar stil
irec la is th lowest leve of co pute flight control. Pilo contro surfaces unmodified Because ofthe large number offailures required to degrad to di ec la.w,it is unlikely to occu during normal flight
encountere when th landin gear is lo er a. teran in flight degradatio to alternat
In altern te law, he th landin ge is extended th co tr la will degrad to irec law. E C A . M warnin as shown, You will an ddltlcna essaqe on th FD We will stud th late on
Direct la.w,a th na implies, ives direct relationship betwee side stic ovem nt nd th deflection .1 surfaces. In ffect, th A320 beha es like conventional aircraft an contro sensitivit will depend on airspeed
In direct law, ther ar no protection availabl although stal an sp in appropriat speeds
"
"
. " . .
....:.
""""'-
........ ."..
.......
Auto trim is ot available. he crew must trim th aircraft manually. jj SE MA PI
IM is indicate
on th PF
in also lost Al ya
co tr
in irec la wis throug
th ru de pedals
ailures, such as complete loss of flight contro computer po er su ply, th alrcratt will revert to mechanica back-u mode.
itch djustm nt of th HS usin th pitc ri heel provided it er re yellow ydraulic syst is available. To indicate this a."M.ANPITC TR.IMONLY" appear in
chie rudd pe al an heir mech nica linkag to th rudder provided at leas on hydrauli syst is available.
In os case e. by resettin th flight contro co pu er yo il able recove from mechanical backup to ithe lter at or irec la dependin on th type offailure. We will su mary il di fe en laws an thei associated protections
In or al la al th protections ar avallable.
_,
In alternat law, th pitc attitude prot ctio an he an angl protection ar lost Load factor li it tion is kept High an lo spee stabilitie re introduced.
_,
In alternat
la.wwithout reduce ig spee stabilitie ar also lost he only remainin load factor limitation.
rotectio
is th
In direct law, al th protection ccnventlcnel aircraft
In mechanical ackup, protection exists he itch cont ol is perf rmed ia he pitc trim whee nd th late al cont ol th ough th rudder pedals thanks to thei rnecharrlcal llnkaqes provided th appropriat hydrauli system ar avallable.
