### ^!Er>\RTMENTO F •'NSPORTATIO N b fOPERATION S Co n todogust o <^--'L:C- ! P 

### 3 = 3 U 

# HpraTFATJO N 

# ^^vianc a

Bogota , Novembe r23 , 201 0 A301000000-69 5 T o Docke t Operation , U. S Departmen t o f Transportatio n Wes t Buildin g Groun d Floor . Roo m W12-140 . 120 0 Ne wJerse yAvenue . SE . Washington . D C 20590 . US A SUBJECT : Exemptio n reques t fo ra portio n o f th e Federa l Aviatio n

Regulatio n Appendi xM t o Par t 121—Airplan e Fligh t Recorde r fo rAirbu s A319/A32 0 Flee t operate d b yAvianc a Airlines . REF:FA R rule s amendment s 25-124 , 121-33 8 Issue d o n March , 7 200 8 - Revision s t o Cockpi t Voic e Recorde r(CVR ) an d Digita l Fligh t Dat a Recorde rRegulation s (DFDR) , fina l Rule . Aerovia s de l Continent e Americano , Avianc a Airlines , a FA R 12 9 Operato r hereb yrequest s a n exemptio n t o Appendi xM t o Par t 121—Airplan e Fligh t Recorde rSpecification s ite m 1 8 : "Fo ral l aircraf t manufacture d o n o rafte r Decembe r6 , 2010 , th e second s pe rsamplin g interva l i s 0.125 . Eac h inpu t mus t b e recorde d a t thi s rate . Alternatel ysamplin g input s (interleaving ) t o mee t thi s samplin g interva l i s prohibited" . Se e attache d document , Appendi xM t o Par t 121-Airplan e Recordin g Specifications . Th e regulatio n i s applicabl e t o al l aircraf t operate d unde rFAAoperationa l regulatio n (N-registere d A/ C o runde rAirworthines s Authoritie s followin g FA A operationa l rules) , throug h FA APar t 121 , o r129 . Avianc a i s plannin g t o receiv e it s 19' " Airbu s A320-21 4 aircraf t MS N 456 7 deliver yo n mi d January , 2011 . However , accordin g t o th e informatio n w e hav e receive d fro m Airbus , ther e hav e bee n som e problem s wit h th e certificatio n o f Sage m FDIMU , whic h wil l preven t thi s airplan e t o compl ywit h th e requirement s o f thi s regulation . Therefore , Avianc a request s a n temporaryexemptio n t o thi s rul e unti l th e airplan e ca n b e retrofitte d wit h approve d modification s whic h wil l b e no t late r tha n Jun e 2011 , i n accordanc e wit h th e informatio n provide d b yth e OE M (Airbu s an d Sagem) . Pleas e se e Attached , Documen t Airbu s Lette ran d Sage m E-Mai l informin g th e statu s o f th e certificatio n proces s o f tha t equipment .

### Thi s exemptio n woul d no t jeopardiz e airplan e safet ybecaus e th e curren t equipmen t i s stil l complian t wit h th e FD R mandator yrecordin g parameter s a s requiredb yFA R 121.34 4 Thi s exemptio n i s i n interes t o fth e Unite d State s publi cbecaus e i t wil l allo wth e airlin e t o improv e th e curren t sen/ic e standar d du e th e incorporatio n o f thes e newl ymanufacture d airplane s tha t carr yU. S tourist , U.S . busines s peopl e an d U. S manufacture d goods . An ydisruptio n o fth e service s performe d b yAvianc a Airline s woul d undoubtedl y hav e a n advers e effec t o n th e U. S interest s i n Colombia . I fyo u hav e question s o ri t i s necessar ytha t w e provid e furthe rinformation , pleas e contac t us . Sincerely ,

-ui s Albert o Valenci a Avianc a Qualit yDirecto r Lvalencia@avianca.co m Phone : (57-1 ) 41 3 987 3 Fax : (57-1 ) 41 3 834 0 CC : Mr . Alla n McHenry . Principa l Avionic s Inspecto rAvianc a Federa l Aviatio n Administration . Miam i Internationa l Fiel d Offic e Mr . Larr yCampbel l Principa l Maintenanc e inspecto rAvianc a Federa l Aviatio n Administration . Miam i Internationa l Fiel d Offic e

## AIRBU S

FHO M Eduard o HURTAD O DAT S Novembe r26 , 201 0 PHON E +33(0) 5 6 7 1 9 0 0 3 3 FA X +33(0) 5 6 1 9 3 4 3 1 6 E-MAI L Eduardo.Hurtado@airbus.co m OU R REFERENC E SA03CT100636 3 YOU R REFERENC E M rLui s Albert o VALENCI A AVIANC AQUALIT YDIRECTO R AVIANC A Avenid a E l dorad o #106-7 4 Hanga r2 Ris e 2 Bogot a Colombi a SUBJEC T: FA R Amendment s 25-124/121-338 : Complianc e statu s updat e o n ne w FA ARecordin g Regulation s fo rAVIANC Aupcomin g A32 0 famil van d A33 0 productio n aircrafts . Dea rMr . Valencia , W e w/oul d lik e t o giv e yo u a n updat e o n th e complianc e statu s o n th e ne wFAAregulation , FA R Amendment s 25-124 , 121-33 8 o n bot h you rSingl e Aisl e an d Lon g Rang e existin g definitions : A32 0 famil v I n orde rt o compl yi n it s entiret ywit h th e ne wregulation , Airbu s ha s define d th e belo wsolution s o n A32 0 family : Separat e container s / Dua l Combinatio n Reliabl e powe rbu s /

N o Singl e Electrica l Failur e shoul d disabl e bot h 1)CVR/DFD R 2 ) CVR/DFD R recorder s 3 ) CV R 1 0 minute s Independen t Powe rSuppl y 4 ) Data-lin k

Recording : FA Arequest s AT C data-lin k communication s shal l b e recorde d i f AT C data-lin k

communicatio n equipmen t i s installe d o n th e A/C (FANS ) 5 ) Increase d DFD R Recordin g Rate s t o 8 sample s pe rsecond s fo rFligh t Controls . You rcurren t A32 0 aircraf t specificatio n alread yincorporate s th e solution s 1 ) thr u 3) . Solutio n 4 ) doe s no t appl yi n you rcas e a s i t i s limite d t o AT C data-lin k (FANS ) equippe d A/C s (FAN S A/ B i s optiona l o n A32 0 famil yan d i t i s no t part o fAvianc a A32 0 aircraf t specification) . O n th e othe rhand , I a m afrai d tha t w e wil l no t b e abl e t o compl ywit h th e requirement s associate d t o th e th e 5t h (5 ) solutio n du e t o a dela yo n th e certificatio n schedul e o f th e ne wFDIM U s wcapabl e o f 1,02 4 w/ s fro m SAGEM . I n fact , w e hav e jus t bee n acquitte d tha t i t wil l b e no wdelaye d b ythre e (3 ) month s (fro m Octobe r201 0 t o January2011 ) an d consequentl yi t wil l n o longe rb e possibl e t o instal l i t i n th e upcomin g productio n Avianc a A32 0 deliverie s MSN s 4547 , an d 456 7 (t o b e delivere d fro m ou rproductio n facilitie s i n Decembe r2010 , an d Januar y201 1 respectively ) a s initiall ytargete d s o a s t o mee t complianc e wit h th e ne wFAArecordin g rul e regulatio n i n it s sub-requiremen t abou t th e increase d DFD R recordin g rate s whic h become s effectiv e o n Decembe r6th , 2010 . Base d o n thi s revise d certificatio n schedule , th e firs t AVIANC Aproductio n A32 0 aircraf t t o b e full y complian t wit h th e aforementione d regulatio n wil l b e MS N 4599 , whic h wil l b e delivere d i n February 2011 . AIRBUS , ANEAD S COMPAM Y AIKBU S S.AS . SOCIET E PA R ACTION S SIUPUFIE E A U CAPITA L D E 2.704.37 S EUROS PCS . TOULOUS E C 38 3 47 4 81 4 I . PON D POIN TMAURIC E BELLONT E 3 f70 7 BLASNA C CEDE X FRANC E PHON E +3 3 (0) 5 6 ( 9 3 3 3 3 3

## AIRBU S
A s soo n a s w e successfull ymanag e t o certif yth e ne wSAGE M FDIMU , w e wil l launc h th e associate d Servic e Bulletin s s o a s t o upgrad e you raircraft s t o th e lates t FDIM U s w(softwar e upgrad e only) , an d i n additio n fo rth e activatio n o f 8 sample s pe rsecond s fo rFligh t Control s capabilit yo n th e FDR . I t i s importan t t o remar k

a t thi s tim e tha t th e tw o mentione d partiall ynon-complianc e aircraft s wil l alread y includ e i n thei rdefinition s th e lates t FDR , an d FCD C standard s s o a s t o compl ywit h thi s regulation . Availabilit yo fth e S B woul d b e b yJun e 201 1 subjec t t o th e successfu l productio n certification . A33 0 aircraf t Similarly , i n orde rt o compl yi n it s entiret ywit h th e ne wregulation , Airbu s ha s define d th e belo w solution s o n A33 0 aircraft : 1 ) CVR/DFD R - Separat e container s / Dua l Combinatio n 2 ) CVR/DFD R - Reliabl e powe rbu s / N o Singl e Electrica l Failur e shoul d disabl e bot h recorder s 3 ) CV R 1 0 minute s Independen t Powe rSuppl y 4 ) Data-lin k

Recording : FAArequest s AT C data-lin k communication s shal l b e recorde d i f AT C data-lin k

communicatio n equipmen t i s installe d o n th e A/C (FANS ) 5 ) Increase d DFD R Recordin g Rate s t o 8 sample s pe rsecond s fo rFligh t Controls . You rcurren t A33 0 configuratio n alread yinclude s th e solution s 1 ) thr u 3) . Fo rsolutio n 5 ) w e ar e stil l i n goo d trac k

t o targe t MS N 120 8 (nex t productio n A33 0 Avianc a delivery- Marc h 2011) : o n thi s aircraf t w e ar e alread yincludin g th e ne wFDIMU , an d FD R bot h capabl e o f 1,02 4 w/ s recording , an d th e sol e outstandin g modificatio n t o b e confirme d i s fo rth e ne wFCD C L2 1 standar d (thi s shal l b e confirme d b yth e 3 o fDecembe rlatest) . Onc e confirmed , al l you rupcomin g A33 0 aircraft s woul d compl ywit h th e requirement s associate d t o 5) . Th e majo rare a i n whic h w e ar e facin g certificatio n delay s i s fo rth e modification s neede d s o a s t o compl ywit h th e requirement s o f th e CV R solutio n 4) , a s i n thi s cas e you rA33 0 aircraft , compare d t o th e SAs , woul d b e oblige d t o compl ywit h sectio n 4 o fthi s rulemakin g a s i t use s Dat a Lin k - FAN S A+ove rACARS . Th e non-complianc e area s are : 4.1 . Ne wSSCV R installatio n (ste p 2) : Th e CV R fro m Honeywel l i s targete d t o b e certifie d i n firs t quarte ro f 2011 . 4. 2 Ne wATS U standar d (hardwar e & software ) Th e ne wATS U hardwar e an d softwar e i s schedul e fo rcertificatio n planne d b y4Q2011 . 4. 3 Activatio n o f th e data-lin k functio n b ypi n programmin g o n ATSU . Thi s wil l b e propose d certifie d a s soo n a s al l th e relate d computer s standar d (ATSU , SSCVR , SDAC , FWC ) ar e available . Base d o n th e above , w e se e stron g indication s tha t al l you rupcomin g A33 0 deliverie s wil l compl y wit h section s 1) , 2) , 3) , an d 5 ) (thi s late rt o b e confirme d a t th e en d o f nex t week) , wherea s I a m afrai d yo u woul d nee d t o see k a waive rfo rexemptio n fo rth e FD R requiremen t fo rprocutio n aircraft s 1208 , 122 4 (Ma y201 1 delivery) , an d potentiall yMS N 127 9 (January201 2 delivery ) i n cas e th e ne w CV R fro m Honeywel l i s no t certifie d o n time . Th e availabilit yo f th e SB s t o cove rsection s 4. 1 thr u 4. 3 woul d b e b yearl ysecon d quarte r2012 . Res t assure d tha t w e ar e makin g bes t effort s t o improv e th e lead-time s fo rcertification , an d tha t w e wil l kee p yo u update d o n th e progres s made .

AIRBUS , ANEAD S COMPAN YAIRBU S SAS . 1 . RON D POIN TMAURIC E BELLONT E SOCIET E PA R ACTION S SIMPLIFIE E 3)70 7 BLAONA C CEDE X A U CAPITA L D E 2.704.37 5 EURO S FRANC E R.CS . TOULOUS E C 38 3 47 < 81 4 PHON E tS J (0) 5 8 1 9 3 3 3 3 3

## AIRBU S I n ligh t ofth e abov

e mentione d situation , Airbu s recommend s Avianca t o contac t a t you rearliest opportunit yyou rloca l airworthines s authoritie s t o infor m the m abou t th e upcomin g non-compliance situation , an d i f possibl e see k a waive rfo rexemptio n fo rth e non-compliance sub-parts . Do no t hesitat e t o contac

t m e fo radditiona l information . Your s Sincerely ,

E . HURTAD O Customisatio n Directo r Custome rAffair s
Copy : (withou t end. ) Avianca - M rDavi d ARAN A Avianc a - M rRicard o FLORE Z Avianc a - M rJaive rQUINTAN A Airbu s - M rDavi d Melo t Airbu s - M rThoma s Fix y Airbu s - M rAlexandr e Van-Scho r Airbu s - Mr s Regin e Sobotk a Airbu s - M rRemai n Legas t Airbu s - M rJua n Jos e Menoss i Airbu s - M rPete rAnder s

AIRBUS , A N EAD S COMPAN YAIRBU S S.AS . 1 , RON D POIN TMAURIC E BELLONT E SOCIET E PA R ACTION S SIMPLIFIE E 3170 7 BLAGNA C CEDE X A U CAPITA L D E 2704.37 5 EURO S FRANC E RC.S . TOULOUS E C 38 3 <7 4 81 4 PHON E +3 3 (0) S 6 ( 9 3 3 3 3 3

# I

### e-CF R Dat a i s curren t a s o f Novembe r19 , 201 0 Titl e 14 : Aeronautic s an d Spac e PAR T121-OPERATIN G REOlilREMENTS : DOMESTIC . FLA G AN D SUPPLEMENTA L OPERATION S Brows e Previou s | Brows e Next Appendi xM t o Par t 121—Airplan e Fligli t Recorde rSpecification s Th e recorde d value s mus t mee t th e designate d range , resolutio n an d accurac yrequirement s durin g stati can d dynami cconditions . Dynami cconditio n mean s th e paramete ri s experiencin g chang e a t th e maximu m rat e attainable , includin g th e maximu m rat e o freversal . Al l dat a recorde d mus t b e correlate d i n tim e t o withi n on e secon d 

### Parameter s 1 . Tim e o r relativ e time s counts. '

2 . Pressur e Altitud e

3 . Indicate dairspee do r Calibrate dairspee d
4 . Headin g (Primary flight cre w reference )

5 . Norma l acceleratio n (vertical) ^ Rang e 2 4 Hrs , 0 t o 409 5

-100 0 f t t o max certificate d altitud e o f aircraft . +500 0 ft 5 0 KIA S or minimu m valu e to Max Vsot o 1. 2 V.D 0-360 ° an d Discret e "true " o r "mag "

-3 g t o +6 g Accurac y

(senso r input ) ±0.125 % pe r hou r

±10 0 to ±70 0 ft (se e table , IS O CI24 a o r IS O C5la ) ±5 % an d ±3 %
±2 °

±1 % o f max rang e excludin g datu merro r Second s pe r

samplin g interva l 4

1

1

1

0.12 5 Resolutio n

1 se c

5't o 35 '

Ik t

0.5 °

0.004 g Remark s

UT C tim e preferre dwhe n available . Coun t increment s eac h4 second s o f

syste m operation . Dat ashoul db e obtaine dfromth e ai r dat acompute r whe npracticable . Dat ashoul db e obtaine dfromth e ai r dat acompute r whe npracticable . Whe ntru e o r magneti c headin g canb e selecte da s th e primary headin g reference , adiscret e indicatin g selectio nmus t

b e recorded .

### 6 . Pitc hAttitud e

7 . Rol l attitude ^
8 . Manual Radi o Transmitte r Keyin g o r CVR/DFD R synchronizatio nreferenc e

9 . Thrust/powe r

o neac h engine—^primar

y flight cre w referenc e

10 . Autopilo t

Engagemen t 11 . Longitudina l Acceleratio n ±75 °
±180 °
On-Of f (Discrete ) Non e

Ful l rang e forward

Discret e "on " o r "of f ±l g o f

±5 % ±2 °
±2 °

±2 %

±1.5 % max . rang e excludin g datu merro r 1 o r

0.2 5 for airplane s operate dunde r §121.344(f

) 1 or 0. 5 for airplane s operate dunde r §121.344(f

) 1

1 (per engine )

1 0.2 5 0.5 °

0. 5

0.3 % o f ful l rang e

0.004 g A samplin g rat e

o f 0.2 5 i s recommended . A samplin g rat e o f 0. 5 i s recommended . Preferabl y eac h cre w membe r

bu t on e discret e acceptabl e for

al l transmissio n provide dth e CVR/FD Rsyste m complie s with TSOC124aCV R synchronizatio n requirement s (paragrap h4.2. 1 ED-55) . Sufficient parameter s (e.g . EPR,Nlo r Torque , NP ) a s appropriat e t o th e particular engin e bein g recorde dt o determin e power inforwardan d revers e thrust , includin g potentia l overspee d condition .

### 12a . Pitc hcontrol(s ) positio n

(nonfly-by-wire systems).' ^

12b . Pitc hcontrol(s ) positio n (fly-by-wire systems).'" ^
13a . Lateral contro l position(s ) (nonfly-by wire).' ^ Ful l Rang e

Ful l Rang e

Ful l Rang e o f

±5 % ±2 ° unles s higher accurac y uniquel y require d

±2 ° unles s highe r accurac y uniquel y require d ±2 ° unles s highe r accurac y uniquel y require d 0. 5 or

0.2 5 fo r airplane s operate dunde r §121.344(f

)

0. 5 o r 0.2 5 for airplane s operate dunde r §121.344(f

) 0. 5 or 0.2 5 for airplane s operate dunde r §121.344(f

) 0.5 % o f full rang e

0.2 % o f full rang e 0.2 % o f fiill rang e Fo r

airplane s that hav e aflight contro l breakawa y capability that allow s eithe r

pilo t to operat e th e control s independently , recordboth contro l inputs . Th e contro l input s ma y b e sample d alternatel y onc e per secon dt o produc e th e samplin g interval of0.5or0.25,a s applicable .

Fo r airplane s that hav e aflight contro l breakaway capability that allow s eithe r

pilo t t o operat e th e control s independently , recordboth contro l inputs . Th e contro l input s may b e sample d alternatel y onc e pe r secon dt o produc e th e samplin g interval of0.5or0.25,a s applicable .

### 13b . Lateral contro l

position(s ) (fly-by-wire).'*' *
14a . Ya w contro l position(s ) (nonfly-by-wire).^' *

14b . Yaw contro l position(s ) (fly-by-wire).' *

, 

### 15 . Pitc hcontro l surface(s ) position.^' * ... . - 

### Ful l Rang e

Ful l Rang e

Ful l Rang e

Ful l Rang e ±2 ° unles s

highe r accurac y uniquel y require d ±2 ° unles s highe r accurac y uniquel y require d

±2 ° unles s highe r accurac y uniquel y require d ±2 ° unles s highe r accurac y uniquel y require d 0. 5 or

0.2 5 for airplane s operate dunde r §121.344(f

) 0. 5

0. 5

0. 5 o r 0.2 5 for airplane s operate dunde r §121.344(f

) 0.2 % o f full range . 0.3 % o f full rang e

0.2 % o f full rang e 0.3 % o f ful l rang e Fo r

airplane s that hav e aflight contro l breakaway capability that allow s eithe r

pilo t t o operat e th e control s independently , recordboth contro l inputs . Th e contro l input s ma y b e sample d alternatel y onc e pe r secon dt o produc e th e samplin g interval ofO.5 .

Fo r airplane s fittedwit h multipl e or

spli t surfaces , a suitabl e combinatio no f input s i s acceptabl e i nlieu o f recordin g eac h surfac e separately . Th e contro l surface s may b e sample d alternatel y onc e per secon dt o produc e th e

### 16 . Lateral contro l surface(s )

position.^' *

17 . Ya w contro l surface(s ) position.*' *

18 . Lateral Acceleratio n

19 . Pitc hTri mSurfac e Positio n Ful l Rang e

Ful l Rang e

±l g

Ful l Rang e ±2 ° unles s

highe r accurac y uniquel y require d

±2 ° unles s highe r accurac y uniquel y require d

±1.5 % max . rang e excludin g datu merro r o f ±5 % ±3 ° Unles s Highe r Accurac y Uniquel y 0. 5 o r

0.2 5 for airplane s operate dunde r §121.344(f

)

0. 5

0.2 5

1 0.3 % o f

full rang e

0.2 % o f full rang e

0.004 g

0.6 % o f full rang e samplin g interval

of0.5or0.25,a s applicable . A suitabl e combinatio no f surfac e positio n sensor s i s acceptabl e i nlieu o f recordin g eac h surfac e separately . Th e contro l surface s may b e sample d alternatel y to produc e th e samplin g interval of0.5or0.25 , a s applicable . Fo r airplane s wit

h multipl e or

spli t surfaces , a suitabl e combinatio no f surfac e positio n sensor s i s acceptabl e i nlie u o f recordin g eac h surfac e separately . Th e contro l surface s ma y b e sample d alternatel y to produc e th e samplin g interval o f 0.5 .

### 20 . Trailin g Edg e Flap or

Cockpi t Contro l Selection.' "

21 . Leadin g Edg e Flap o r Cockpi t Contro l Selection. "

22 . Eac hThrus t

Reverse r Positio n(o r

equivalen t

for propelle r airplane )
23 . Groun dspoiler

positio n o r brak e selection^ ^
24 . Outsid e Ai r

Temperatur e or Total Ai r Temperature.'' ^ 25 . Autopilot/Autothrottle/AFC S Mod e an dEngagemen t Statu s Ful l Rang e or Eac h Positio n (discrete )

Ful l Rang e o r Eac h Discret e Positio n

Stowed , In Transit , an d Revers e (Discrete ) Ful l rang e o r eac h positio n (discrete ) -5 0 ° C t o +9 0 ° C Asuitabl e combinatio n o f discrete s Require d

±3 ° or a s Pilot' s indicato r

±3 ° o r a s Pilot' s indicato r an d sufficient t o determin e eac hdiscret e positio n

±2 ° Unles s highe r accurac y uniquel y require d ±2° C 2

2

1 (pe r engine )

1 or 0. 5 for airplane s operate dunde r §121.344(f

) 2 1 0.5 % o f

full rang e

0.5 % o f fiill rang e

0.5 % o f ftill rang e 0. 3 ° C Flap positio nan d

cockpi t contro l ma y eac hb e sample dat

4 secon dintervals , t o giv e adat a poin t every 2 seconds . Lef t an drigh t sides , or flap positio nan d cockpi t contro l ma y eac hb e sample dat

4 secon dintervals , s o a s t o giv e a dat apoin t ever y 2 seconds . Turbo-jet— 2 discrete s enabl e th e 3 state s t o b e determined . Turbo-prop — discrete .

Discrete s shoul d sho w whic h system s are engage dan d whic hprimary mode s ar e controllin g th e flight pat han d spee do f th e aircraft .

### 26 . Radi o Ahitude' "

27 . Localize r

Deviation , ML S Azimuth , o r

GP S Latitud e Deviatio n

28 . Glideslop e Deviation , ML S Elevation , o r

GP S Vertical Deviatio n -2 0 ft t o 2,50 0 ft

±40 0 Microamp s o r availabl e senso r rang e a s installe d ±62 °

±40 0 Microamp s or availabl e senso r rang e a s installe d 0. 9 t o +30 ° ± 2 ft

or ±3 % whicheve r

i s greate r belo w 50 0 ft an d ±5 % abov e 50 0 ft

A s installe d ±3 % recommende d

A s installe d +/3-3 % recommende d 1

1

1 1 ft

+5 % abov e 50 0 ft

0.3 % o f full rang e

0.3 % o f full rang e Fo r

autoland/category 3 operations . Eac hradi o altimete r shoul d b e recorded , bu t arrange ds o that

a t leas t on e i s recorde deac h second . Fo r autoland/category 3 operations . Eac hsyste m shoul db e recorde dbut arrange ds o that

a t leas t on e i s recorde deac h second . It i s no t necessary to recordIL S an d ML S a t th e same time , onl y th e approac hai di n us e nee db e recorded . Fo r autoland/category 3 operations . Eac hsyste m shoul db e recorde dbu t arrange ds o that

at leas t on e i s recorde deac h second . It i s no t necessary t o recor dIL S an d ML S a t th e same time , onl y th e approac hai di n us e nee db e recorded .

### 29 . Marke r Beaco nPassag e 30 . Maste r

Warnin g

31 . Air/groun dsenso r (primary airplan e syste m referenc e nos e o r

mai ngear ) 32 . Angl e o f

Attac k (I f measure ddirectly )

33 . Hydrauli c Pressur e Low , Eac hSyste m

34 . Groundspee d
35 . GPW S (groun d proximity warnin g system ) Discret e "on " or "of f Discret e

Discret e "air " o r "ground " A s installe d

Discret e o r availabl e senso r range , "low " o r "normal " A s Installe d
Discret e "warning " or"of f A s installe d

±5 %

Mos t Accurat e System s Installe d 1

1

1 (0.2 5 recommended ) 2 or 0. 5 for airplane s operate dunde r §121.344(f

)

2

1
1 0.3 % o f

full rang e

0.5 % o f fiill rang e

0.2 % o f full rang e A singl e discret e

i s acceptabl e fo

r al l markers . Recor dth e maste r warnin g an d recor deac h"red " warnin g that carmo t b e determine dfrom other parameter s or fromth e cockpi t voic e recorder .
Iflef t an dright sensor s are available , eac h may b e recorde d a t 4 o r 1 secon d intervals , a s appropriate , s o a s t o giv e adat a poin t a t 2 second s or 0. 5 second , a s required .

A suitabl e combinatio no f discrete s unles s recorde r capacity i s limite di n whic hcas e a

### 36 . Landin g Gea r Positio no r Landin g gea

r cockpi t contro l selectio n 37 . Drif t Angle.' ^ 38 . Win dSpee dan d Directio n 39 . Latitud e an dLongitud e

40 . Stic k shaker an dpushe r activatio n
41 . Windshear

Detectio n 42 . Throttle/powe r

Leve r 1 position.' ^ 43 . Additiona l Engin e Parameter s Discret e
A s installe d A s installe d A s installe d

Discrete(s ) "on " o r "of f Discret e "warning " or"of f Ful l Rang e
A s installe d A s installe d

A s installe d A s installe d

±2 %
A s installe d 4

4 4 4

1

1 1 for eac h leve r Eac hengin e eac hsecon d 0.1 °

1 knot , an d 1.0 ° 0.002° , o r a s installe d

2%offtil l rang e 2%offtil l rang e singl e discret e fo r al l mode s i s acceptable . A suitabl e combinatio no f discrete s shoul d b e recorded .

Provide db y th e Primary Navigatio n Syste m Reference . Where capacity permit s Latitude/longitud e resolutio nshoul d b e 0.0002° . A suitabl e combinatio no f discrete s t o detenriin e activation .
Fo r airplane s with non-mechanical l

y linke dcockpi t engin e controls . Where capacity permits , th e preferre dpriority i s indicate d vibratio nlevel , N2 , EGT , Fue l Flow , Fue l Cut of f lever positio n an dN3 , unles s engin e manufacturer

### 44 . Traffi c Alert an d Collisio nAvoidanc e Syste m (TCAS )

45 . DM E1 an d2 Distanc e 46 . Na v 1 an d2 Selecte d Frequenc y 47 . Selecte dbarometri c settin g 48 . Selecte dAltitud e 49 . Selecte dspee d 50 . Selecte dMac h 51 . Selecte dvertica l spee d 52 . Selecte dheadin g 53 . Selecte dflight

path 54 . Selecte ddecisio nheigh t 55 . EFI S display forma

t Discrete s

0-20 0 N M Ful l Rang e Ful l Rang e Ful l Rang e Ful l Rang e Ful l Rang e Ful l Rang e Ful l Rang e Ful l Rang e Ful l Rang e Discrete(s ) A s installe d

A s installe d A s installe d
±5 % ±5 % ±5 % ±5 % ±5 % ±5 % ±5 % ±5 % 1

4 4 ( 1 pe r 6 4 sec. )

6 4 4 IN M

0.2 % o f full rang e 100 ft 1 kno t .0 1 lOOft/mi n 1 ° 1 ° 

### 1f t recommend s otherwise . A suitabl e combinatio no f discrete s shoul d be recorde dt o determin e th e statu s of — Combine d Control , Vertical Control , U p Advisory , an d Dow nAdvisory , (re f ARIN C Characteristi c 73 5 Attachmen t

6E , TCA S VERTICA LRA DAT A OUTPU T WORD. ) 1 mil e Sufficient t o determin e selecte d frequenc y

Discrete s shoul d sho w th e display syste mstatu s (e.g. , off , normal , fail , composite , sector , plan , nav

### 56 . Multi-fiinction/Engin e

Alert s Display forma

t

57 . Thrus t command.' ^ 58 . Thrus t targe t 59 . Fue l quantity i nC Gtri m tank 60 . Primary Navigatio n Syste mReferenc e

61 . Ic e Detectio n 62 . Engin e warnin g eac h engin e vibratio n 63 . Engin e warnin g eac h engin e ove r

temp 64 . Engin e warnin g eac h |engin e oi l pressur e lo w 65 . Engin e warnin g eac h [engine over

spee d 66 . Ya w Tri mSurfac e Positio n Discrete(s )

Ful l Rang e Ful l Rang e Ful l Rang e Discret e GPS , INS , VOR/DME , MLS , Loran C , Omega , Localize r Glideslop e Discret e "ice " o r "n o ice " Discret e Discret e Discret e Discret e Ful l Rang e ±2 %

±2 % ±5 %

±3% ) Unles s Highe r Accurac y 4

2 4 ( 1 pe r 6 4 sec. ) 4

4 1 1 1 1 2 2 % o f

fiill rang e 2 % o f full rang e l%offtil l rang e

0.3 % o f full rang e aids , weathe r

radar , range , copy . Discrete s shoul d sho w th e display syste mstatu s (e.g. , off , normal , fail , an dth e identity o f

display page s for emergenc y procedures , nee d no t b e recorded . |

A suitabl e combinatio no f discrete s t o determin e th e Primary Navigatio n Syste mreference .

### 67 . Rol l Tri mSurfac e

Positio n 68 . Brake Pressur e (lef

t an d right ) 69 . Brake Pedal Applicatio n (lef t an dright ) 70 . Yaw or

sidesli p angl e 71 . Engin e blee dvalv e positio n 72 . De-icin g o r

anti-icin g syste mselectio n 73 . Compute dcente r

o f gravity 74 . A C electrical bu s statu s 75 . D C electrica l bu s statu s 7 6 APU blee dvalv e positio n 77 . Hydrauli c Pressur e (eac h system ) 78 . Los s o f

cabi npressur e 79 . Compute r

failure (critica l Ful l Rang e

A s installe d
Discrete or Analo g "applied " or "of f Ful l Rang e Discret e "open " o r "closed " Discret e "on " o r "of f Ful l Rang e Discret e "power " o r "of f Discret e "power " or "of f Discret e "open " or "closed " Ful l rang e Discret e "loss " o r "normal " Discret e Uniquel y

Require d ±3 % Unles s Highe r Accurac y Uniquel y Require d ±5 %
±5 % (Analog ) ±5 %

±5 %

±5 % 2

1
1
1 4 4 ( 1 pe r 6 4 sec. ) 4 4 4 2 1 4 0.3 % o f

full rang e

0.5 °

1 % o f fiill rang e

100 ps i T o determin e

brakin g effor

t applie db y pilot s or b y autobrakes . T o determin e brakin g applie d b y pilots .

Eac hbus . Eac hbus .

### flight

an dengin e contro l systems ) 80 . Heads-u p display (whe n a ninformatio nsourc e i s installed ) 81 . Para-visual display (whe na ninformatio nsourc e i s installed ) 82 . Cockpi t

tri mcontro l inpu t position—pitc h

83 . Cockpi t

tri mcontro l inpu t position—rol l

84 . Cockpi t

tri mcontro l inpu t position—ya w

85 . Trailin g edg e flap an d cockpi t flap contro l positio n "fail " or

"normal " Discrete(s ) "on " or "of f Discrete(s ) "on " or "of f Ful l Rang e

Ful l Rang e

Ful l rang e

Ful l Rang e ±5 %

±5 %

±5 %

±5 % 4

1

1

1

2 0.2 % o f

full rang e

0.7 % o f full rang e

0.3 % o f full rang e

0.5 % o f full rang e Where

mechanical mean s fo r contro l input s ar e no t available , cockpi t display tri mposition s shoul db e recorded . Where mechanical mean s for contro l input s are no t available, cockpi t display tri mpositio n shoul db e recorded . Where mechanical mean s fo r contro l inpu t are no t available , cockpi t display tri mposition s shoul db e recorded . Trailin g edg e flaps an dcockpi t flap contro l positio nma

y eac h b e sample d alternatel y a

t 4 secon dinterval s to provid e a sampl e eac h0. 5 second .

### 86 . Leadin g edg e flap an d

cockpi t flap contro l positio n 87 . Groun dspoile r

positio n an dspee dbrak e selectio n 88 . Al l cockpi t

flight contro l inpu t force s (contro l wheel , contro l column , rudde r pedal)'*' ^

89 . Ya w dampe r

statu s 90 . Yaw dampe r

comman d 91 . Standb y rudde r

valv e statu s Ful l Rang e or Discret e Ful l rang e or discret e Ful l rang e Contro l whee l ±7 0 lb s Contro l colum n±8 5 lb s Rudder pedal ±16 5 lb s

Discret e (on/off ) Ful l rang e Discret e ±5 %

±5 % ±5 %

0. 5 A s installe d 0. 5 1

0. 5 1

0. 5 0.5 % o f

full rang e 0.3 % o f ful l rang e 0.3 % o f fiill rang e

1 % o f full rang e Fo r

fly-by-wire flight contro l systems , wher e flight contro l surfac e positio ni s afunctio no f

th e displacemen t

o f th e contro l inpu t devic e only , i t

i s no t necessary t o recordthi s parameter . Fo r airplane s that hav e aflight contro l break away capability that allow s either pilo t t o operat e th e contro l independently , recordboth contro l forc e inputs . Th e contro l forc e input s ma y b e sample d alternatel y onc e pe r 2 second s t o produc e th e samplin g interval ofl .

'Fo rA30 0 B2/B 4 airplanes , resolution= 6 seconds .

^^Fo rA330/A34 0 serie s airplanes , resolution=0.703° . ¥o rA318/A319/A320/A32 1 serie s airplanes , resolution=0.275 % (0.088''>0.064°) . Fo rA330/A34 0 serie s airplanes , resolution=2.20%(0.703">0.064* ) •'ForA318/A319/A320/A32 1 serie s airplanes , resolution=0.22 % (0.088°> 0 080°) . Fo rA330/A34 0 serie s airplanes , resolution=1.76% (0.703°>0.080°) . ^Fo rA330/A34 0 serie s airplanes , resolutio n = 1.18 % (0.703'>0.120°) . °Fo rA330/A34 Q serie s airplanes , resolution=0.783 % (0.352">0.090°) . 'Fo rA330/A34 0 serie s airplanes , ailero n resolutio n = 0.704% {0.352">0.100'') . Fo rA330/A34 0 serie s airplanes , spoile rresolutio n = 1.406 % (0.703*>0.100') . "Fo rA330/A34 0 serie s airplanes , resolution=0.30 % {0.176°>0.12'') . Fo rA330/A34 0 serie s airplanes , second s pe rsamplin g interval= 1 'Fo rB-71 7 serie s airplanes , resolutio n = .005g . Fo rDassaul t F900C/F900E X airplanes , resolutio n = .007g . "Fo rA330/A34 0 serie s airplanes , resolution=1.05 % (0.250°>0.120°) . "Fo rA330/A34 0 serie s airplanes , resolutio n = 1.05 % (0.250*>0.120°) . Fo rA30 0 B2/B 4 serie s airplanes , resolutio n = 0.92 % ( 0 230°>0.125") . "Fo rA330/A34 0 serie s airplanes , spoile rresolutio n = 1.406 % (0.703'>0.100°) . "Fo rA330/A34 0 serie s airplanes , rBSOIution=0.5"C . "Fo rDassaul t F900C/F900E X airplanes . Radi o altitud e resolutio n = 1.2 5 ft. "Fo rA330/A34 0 serie s airplanes , resolutio n = 0.35 2 degrees . '°Fo rA318/A319/A320/A321 serie s airplanes , resolutio n = 4.32% . Fo rA330/A34 0 serie s airplanes , resolutio n i s 3 27 % o fful l rang e fo rthrottl e leve rangl e (TLA) : fo rrevers e ttirust , revers e throttl e leve rangl e (RLA ) resolutio n i s nonlinea rove rth e activ e revers e thrus t range , whic h i s 51.5 4 degree s t o 96.1 4 degrees . Th e resolve d elemen t i s 2. 8 degree s uniforml yove rth e entir e activ e revers e thrus t range , o r2.9 % o fth e ful l rang e valu e o f96.1 4 degrees . "Fo rA318/A319/A320/A321 serie s airplanes , v»it h lA E engines , resolutio n = 2.58% . "Fo ral l aircraf t manufacture d o n o rafte rDecembe r6 , 2010 , th e second s pe rsamplin g interva l i s 0.125 . Eac h inpu t mus t b e recorde d at thi s rate . Alternatel y samplin g input s (interieaving ) t o mee t thi s samplin g interva l i s prohibited . "Fo r73 7 mode l airplane s manufactured betwee n Augus t 19 , 200 0 an d Apri l 6 , 2010 : th e second s pe rsamplin g interva l i s 0. 5 pe rcontro l input ; th e remari^ s regardin g th e samplin g rat e d o no t apply : a singl e contro l whee l forc e transduce rinstalle d o n th e left cabl e contro l i s acceptabl e provide d th e left an d right contro l whee l position s als o ar e recorded . [Doc . No . 28109 , 6 2 F R 38382 , Jul y17 , 1997 : 6 2 F R 48135 , Sept . 12,1997 , a s amende d b yAmdt . 121-271 , 6 4 F R 46120 , Aug . 24 , 1999 : Amdt . 121-278 , 6 5 F R 51745 , Aug . 24 , 2000 : 6 5 F R 81733 , Dec . 27 , 2000 ; Amdt . 121-292 , 6 7 F R 54323 , Aug . 21 , 2002 ; Amdt . 121-300 , 6 8 F R 42936 , Jul y18 , 2003 ; 6 8 F R 50069 , Aug . 20 , 2003 ; 6 8 F R 53877, Sept . 15 , 2003 ; 7 0 F R 41134 , Jul y18 , 2005 ; Amdt . 125-54 , 7 3 F R 12566 , Mar . 7 , 2008 ; Amdt . 121-338 , 7 3 F R 12566 , Mar . 7 , 2008 ; Amdt . 121-342 , 7 3 F R 73179 , Dec . 2 , 2008 ; Amdt . 121-349 , 7 5 F R 17046 , Apr . 5 , 2010 ; Amdt . 121-347 , 7 5 FR7356 , Feb . 19 , 2010 ] Brows e Previou s | Brows e Next

Fo rquestion s o rcomrnent s regardin g e-CF R editoria l content , features , o rdesign , emai l ecfnffinara.gov . Fo rquestion s concernin g e-CF R programmin o an d deliveryIssues , emai l webteami^BopQ.oov .

### Pag e 1 of 1 1 RICARD O ANDRE S FLORE Z TORRE S De : Steve n Irwi n [Steven.lrwin@sagemavionics.com ] Enviad o el : Lunes , 2 2 d e Noviembre d e 201 0 15:0 8 Para : JAIVE R IVA N QUINTAN AOCHOA CC : RICARD O ANDRE S FLORE Z TORRES ; Jaso n Johnso n Asunto : RE : FA

ANE W REGULATION S Hell o Mr . Quintana , I apologiz e fo rlat e response , w e wer e workin g wit h ou rFrance offic e o n gettin g update d information . I've answere d yo u question s belo wi n red : 1 . Wha t i s th e differenc e betwee n th e ol d an d th e ne wFDIMU ? I s i t software only ? Ca n the yb e considere d interchangeable ? Th e difference s betwee n th e ol d FDIM U an d th e ne wFDIM U i s wit h softwar e only . Th e ol d FDIM U ca n b e upgrade d vi a dataloadabl e software . Th e hardwar e unit s ar e considere d interchangeable . 2 . I fth e respons e t o th e firs t questio n i s affirmative , Avianc a woul d lik e SAGE M t o provid e th e Servic e Bulleti n an d Software t o upgrad e thes e units , fre e ofcharge , a s th e delayi s not Airbus' s o rAvianca' s responsibility . Ther e ar e 2 Servic e Bulletins s : 1 equipmen t S B fo rth e S W retrofi t itsel funde rSagem' s responsabilit y+ 1 Airframe rS B fo rth e retrofi t S W instal l o n A/ C unde rAirbu s responsibility . Ou rS B a t equipmen t leve l wil l b e offere d fre e o fcharge . Fo rth e A/ C S B Avianc a shoul d confir m wit h Airbu s fo rth e condition s fo rsoftwar e upgrad e Servic e Bulletins . 3 . Whic h dat e ha s Sage m schedul e i n orde rt o hav e th e newFDIM U certified ? Th e certificatio n dat e no wdepend s o n Airbus . Fligh t test s ar e currentl yongoin g wit h Airbu s an d w e hav e a blac k

labe l hardwar e deliver ywit h S W schedule d o n De c3 , 2010 . Onc e thi s i s accepte d b yAirbu s the n th e S Wupgrad e b ydataloadin g wit h b e dependen t upo n th e actua l Airbu s certificatio n date . Please le t m e kno wi fth e abov e i s acceptabl e o ri fyo u have an yadditiona l questions . Regards , Steve Irwi n 

# ^ SAFRA N Sage m Stev e Irwi n Custome rSuppor

t Manage r Sage m Avionics , Inc . - Safra n grou p Adr. : 280 2 Safra n Dr

. - Gran d Prairie , T

X 7505 2 - US A 

### 11/26/201 0

### Pag e 2 of 1 1 Tel. : +1-972-314-363 4 Gel . : +1-214-228-430 2 eMail : Steven.lrwin@saaemavionics.co m Web : www.sagemavionics.co m Suppor t ou r^•'^'^riWingSjnJtJativ e arij j conside rth e environmen t befor e printin g thi s email . Th e Informatio n containe d i n thi s email , an d an yattachments , i s intende d onl yfo rth e perso n o rentit yt o whic h i t i s addresse d an d ma ycontai n privileged , licensed, and/o rconfidentia l materials . An yretransmission , dissemination , revie wo rothe rus e of , o r takin g an yactio n i n relianc e upo n thi s informatio n b yperson s o rentitie s othe rtha n th e intende d recipien t i s prohibited , withou t prio rwritte n approva l o f Sage m Avionics , Inc . I f yo u receiv e thi s transmissio n i n error , pleas e contac t th e sender , destro ythi s messag e an d delet e th e material s fro m an ycompute rsystem , electroni cstorage , logs , archives , o rothe rmedia . Informatio n i n thi s messag e tha t doe s no t relat e t o th e officia l busines s o f Sage m Avionics , Inc. , shal l b e understoo d a s neithe rprovide d b yno r endorse d b ySage m Avionics , Inc .

From : Steve n Irwi n Sent : Friday , Novembe r12 , 201 0 3:2 7 P M To : 'JQUINTANA@avianca.com ' Cc : RICARD O ANDRE S FLORE Z TORRES ; Jaso n Johnso n Subject : RE : FA

ANE W REGULATION S Hell o Mr . Quintana , I shoul d hav e som e answer s fo ryo u nex t week . Than k yo u fo ryou rpatience . Regards , Stev e Irwi n 

# ^ SAFRA N Sage m Stev e Irwi n Custome rSuppor t Manage r Sage m Avionics , Inc . - Safra n grou p Adr. : 280 2 Safra n Dr . - Gran d Prairie , T X 7505 2 - US A Tel . : +1-972-314-363 4 Cel . : +1-214-228-430 2 eMail : Steven.lnyin@sagemavionics.co m Web : vwvw.sagemavionics.co m Suppor t ou r^'^^nWingSjnitiativ e an d conside rth e environmen t befor e printin g thi s email . 

### 11/26/201 0 J B