## U . S . DEPARTMEN T O FTRANSPORTATION: i ,- , ,- , ^ ^ OFFICEO

FHEARINGS " ' ' ' • ' ^ WASHINGTON , D.C . I NTH EMATTE ROF 

# RECEIVi P EMPIR EFLIGH T ACADEMY JU N" % W ^ Responden

t HEARIN G DOCKE T FDM S NO . FAA-2010-029 0 HONORABL

ERONNI EA . YODE

RB^^^ ' 1^ ^ "^^ ^ 1 3 V ^ E CHIE FADMINISTRATIV

ELA WJUDG E Hearing Date : NON

EASSIGNE

D Hearing Location : NON

EASSIGNE

D RESPONDENTS ' MOTIO NFO RPARTIA LSUMMARY JUDGMEN T COME S NOW , Empir

e Fligh t Academ y (hereinafte

r "Empire") , Responden

t herein , by an dthroughundersigne dcounsel , pursuan t to Rule 13.218(f

) o f th e Procedura

l Rule s (1 4 C.F.R . Par t 13) , andhereb y move s fo

r partia l dismissa l of th e Complain

t a t Coun t III concerning regulator y allegation s o f

1 4 C.F.R . § § 91.405(b) , 91.407(a)(1) , and91.407(a)(2) . Th e pleading s andothe

r supporting documentationestablis htha t ther e ar e no genuine issue s o f materia l fact t o b e resolve dregarding th e allegedviolation s inCount III o f the Complaint . Therefore , Empir

e i s entitle dto judgment

as amatte r o f law . I nsuppor t thereof . Responden

t state s the following :

## PROCEDURA LHISTOR Y Th e Complain t

filedi nthi s matte r

o nApri l 8,2011 , allege s th e following , i npart : 1 . A t al l time s mentione dherein , Empir e Fligh t Academ y wa s th e operato r o f aDiamon d DA-2 0 aircraft , identificatio nnumbe r N383C A (hereinafte r

"th e aircraft") . Complain t 

## atlfl . 2 . O no r abou t Jun e 1,2009 , Empir e Fligh t Academ y proceede dt o operat e th e aircraf t o n aflight t o Republi c Airport , Farmingdale , N Y (hereinafte r "th e Jun e 1 flight"). Complain t

a t T|6 . 3 . Coun t II I o f th e Complain t

allege s th e followin g regulator y violations ; 1 4 C.F.R . § § 91.405(b)' , 91.407(a)(l) ^ an d91.407(a)(2). ^

' Sectio n91.405(b ) state s tha t eac howne r

o r operato r o f anaircraf

t shal l ensur e tha t

maintenanc e personne l mak e appropriat e entrie s i nth e aircraf t maintenanc e record s indicatin g th e aircraf t ha s bee napprove dfo r

retur nt o service . ^ Sectio n91.407(a)(1 ) state s tha t n o perso nma y operat e anaircraf t tha t ha s undergon e maintenance , preventativ e maintenance , rebuilding , o r alteratio nunles s i t

ha s bee napprove dfor returnt o servic e b y aperso nauthorize dunde r Sectio n43. 7 o f

th e Federa l Aviatio nRegulations . Sectio n43.7 , state s th e following , i npart : (b ) Th e holde r

o f amechani c certificat e o r a ninspectio nauthorizatio nma y approv e an aircraft , airframe , aircraf

t engine , propeller , appliance , o r componen t

part for return t o servic e a s provide di nPart 6 5 o f thi s chapter . ^ Sectio n91.407(a)(1 ) state s tha t n o perso nma y operat e a naircraf t tha t ha s undergon e maintenance , preventativ e maintenance , rebuilding , o r alteratio nunles s th e maintenanc e recor d entry require db y Section s 43. 9 o r 43.11 , a s applicable , o f

th e Federa l Aviatio nRegulation s ha s bee nmade .

## ISSU EPRESENTE D

DOE S A GENUIN EISSU EO FMATERIA LFAC T EXIST S CONCERNIN G WHETHE RMAINTENANC EPERSONNE LMAD EA N APPROPRIAT EENTR Y I NTH EAIRCRAF T MAINTENANC ERECORD S INDICATIN GAIRCRAF T N383C A HA D BEE NAPPROVE D FO RRETUR NT O SERVIC EB Y A PERSO N AUTHORIZE D UNDE RSECTIO N43. 7 O FTH EFEDERA LAVIATIO N REGULATION S PRIO RT O TH EFLIGH T O N JUN E1,200 9 PURSUAN T T O 1 4 C.F.R . § 91.405(B) , § 91.407(A)(1) ; AN D § 91.407(A)(2) ?

STANDAR D FO RSUMMAR Y JUDGMEN T A part y seekin g summary judgmen t mus t "demonstrat e tha t

ther e i s n o genuin e issu e o f materia l fac t

i ndisput e an dtha t

th e movin g part y i s entitle dt o judgmen t a s amatte r

o f law. " See , Accurac y I nMedia , Inc. , v . Nationa l Transportatio nSafet y Board , Civi l Actio nNo . 03-0002 4 (CKK) , 3 (D . D.C . 2006) . A s mor e full y describe dbelow , n o genuin e issu e a s t o an y materia l fac t exist s whethe r maintenanc e personne l mad e appropriat e entrie s i nth e aircraf t maintenanc e record s indicatin g that aircraf t N383C A ha dbee napprove dfo r retur nt o servic e prio r

t o th e flight

o nJun e 1 , 2009 , pursuan t t o 91.405(b) , 91.407(a)(1) , an d91.407(a)(2) . Accordingly , sinc e th e pleading s an dothe r supportin g documentatio nestablis htha t ther e ar e n o genuin e issue s a s t o an y materia l fac t t o b e resolve dconcernin g Coun t II I o f th e Complaint , Empir e i s entitle dt o judgmen t a s amatte r

o f law . Therefore , Coun t

II I o f th e Complain t

concernin g th e allege dviolatio no f 1 4 C.F.R . § § 91.405(b) , 91.407(a)(1) , an d91.407(a)(2 ) mus t b e dismisse dwit hprejudice . MATERIA LFACT S NO T I N DISPUT E 1 . O no r abou t Apri l 18 , 2009 , Pau l Masaracchia , Airfram e & Powerplan t (A&P ) mechanic certificat e numbe r 104569374 , performe da100 hou r inspection , includin g inspectio no f

th e landin g gear

o f N383CA , at

a naircraf t tota l tachomete r

tim e o f 932. 1

## houris . Se e Exhibi t A , Affidavi t

o f Chie f Inspecto r Carmin e J . Colaluca , II I a t Exhibi t 1 , pag e 17 , ite m#28 . 2 . O no r abou t Apri l 18,2009 , Pau l Masaracchia , Airfram e & Powerplan t (A&P ) mechani c certificat e numbe r 104569374 , returne dth e aircraf t t o servic e followin g th e 10 0 hou r inspectio nat

a naircraf t tota l tachomete r

tim e o f 932. 1 hours . Specifically , h e determine dtha t

N383C A wa s "airworth y wit hrespec t t o it s maintenanc e condition. " Se e Exhibi t

A at Exhibi t 1 at pag e 40 . 3 . O no r abou t Apri l 19,2009 , Pau l Masaracchia , Airfram e & Powerplan t (A&P ) mechani c certificat e numbe r 104569374 , mad e a naircraf t maintenanc e recor dentry an dreturne dth e aircraf

t t o service. Specifically , h e state dtha t th e aircraf

t was determine dt o b e i n"airworth y condition. " Se e Exhibi t A at Exhibi t 2 . 4 . Thereafter , o no r

abou t May 31,2009 , Same r

Elsayed , Airfram e & Powerplan t (A&P ) mechani c certificat e numbe r 3245675 , returne dN383C A t o servic e followin g a5 0 hou r inspectio nat

a naircraf t tota l tachomete r

tim e o f 982. 2 hours . Specifically , Mr . Elsaye ddetermine dth e aircraf t t o b e i n"airworth y condition. " Se e Exhibi t A at Exhibi t 2 . 5 . Prio r t o th e flight

o nJun e 1 , 2009 , N383CA ha dbee ninspectedan dreturne dt o servic e a s airworth y b y Pau l Masaracchia , Airfram e & Powerplan t (A&P ) mechani c certificat e numbe r 1045693744 , pursuan t

t o 1 4 C.F.R . §43.1 1 .^ Se e Exhibi t A a t Exhibit s 1 & 2 . * Sectio n43.1 1 state s tha t th e perso napprovin g o r

disapprovin g for

retur nt o servic e anaircraft , airframe , aircraf

t engine , propeller , appliance , o r componen t

par t after an y inspectio nperforme di n accordanc e withpar t

91,125 , §135.411(a)(1) , o r §135.41 9 shal l mak e a nentry i nth e maintenanc e recordo f tha t equipmen t

containin g th e followin g information :

## 6 . Prio r t o th e flight

o nJun e 1,2009 , N383C A ha dbee ninspectedan dreturne dt o servic e a s airworth y b y Same r

Elsayed , Airfram e & Powerplan t (A&P ) mechani c certificat e numbe r 324567 5 pursuan t

t o 1 4 C.F.R . §43.11 . Se e Exhibi t A at Exhibi t 2 . ARGUMEN T N O GENUIN EISSU EO FMATERIA LFAC T EXIST S CONCERNIN G WHETHE RMAINTENANC EPERSONNE LMAD EA NAPPROPRIAT EENTR Y I NTH EAIRCRAF T MAINTENANC ERECORD S T O INDICAT ETHA T N383C A HA D BEE NAPPROVE D FO RRETUR NT O SERVIC EB Y A PERSO N AUTHORIZE D UNDE RSECTIO N 43. 7 O FTH EFEDERA LAVIATIO N REGULATION S PRIO RT O TH EFLIGH T O NJUN E1,2009 . Althoug hth e regulator y violation s allege di nCoun t II I o f th e Complain t

sugges t that n o aircraf t maintenanc e entry exist s returnin g N383C A t o servic e prio r t o th e flight

o nJun e 1,2009 , n o genuin e issu e o f

materia l fac t

exist s concernin g th e regulator y charges . Accordingly , Empir e Fligh t Academ y i s entitle dt o judgmen t a s amatte r

o f la w concernin g Coun t

II I o f th e Complain t (i.e. , 1 4 C.F.R . § § 91.405(b) , 91.407(a)(1) , an d91.407(a)(2)) .
(1 ) Th e typ e o f

inspectio nan dabrie f

descriptio no f

th e exten t

o f th e inspection . (2 ) Th e dat e o f

th e inspectio nan daircraf t tota l tim e i nservice . (3 ) Th e signature , th e certificat e number , an dkin do f certificat e hel db y th e perso n approvin g o r

disapprovin g for

returnt o servic e th e aircraft , airframe , aircraf t engine , propeller , appliance , componen t part , o r portion s thereo f (4 ) Excep t

for progressiv e inspections , i f th e aircraf

t i s foimdt o b e airworth y an dapprove d for retur nt o service , th e followin g o r asimilarl y worde dstatement—" I certif y that thi s aircraf t ha s bee ninspecte di naccordanc e with(insert type ) inspectio nan dwas determine d t o b e i nairworth y condition. "

## Rule 13.218(f) , whichgovern s motion s fo r decision , indicate s th e document s tha t ma y be consideredby th e la

w judg e inrulin g onaparty' s motionfo r decision . The Rule provide s a s follows : Th e administrativ e la

w judg e shall gran

t aparty' s motio nfo

r decisio ni f

th e pleadings , depositions , answer s t

o interrogatories , admissions , matter s tha t th e adminisfrative la

w judg e ha s officiall

y noticed , or

evidenc e introducedduring th e hearin g show tha t ther e i s no genuine issu e o f

materia l fac t an dtha t th e part y making th e motio ni s entitle dt o a decisiona s amatte

r o f law . 1 4 C.F.R . 13.218(f)(5) ; see als o I nthe Matter o f HorizonAir

Industries , Inc. , FA

A Orde r No . 96-2 4 (199 6 FA

A LEXI S 205 8 (1996)) . I nAmerica n Airlines , Par t

25 2 Enforcement, Order s 82-6-137 , e t al. , 9 6 C.A.B . 11 4 (1982) , th e Civil Aeronautic s Boar dnotedthat : Th e Boar dha s state dtha

t inaccordanc e wit

hth e Federa

l Rule s of Civi l Procedure , apart

y opposing amotio nfo

r summar y judgment

"ma y no t res t uponth e mer

e allegation s or denial s o f [its ] pleading , but

[its ] response... . mus t

set fort hspecifi c facts showing tha t ther e i s agenuine issu e fo

r trial" . Citing , Aeromerica , Inc. , Orde r 81-8-23 , p.4 . I nthe cas e a

t bar , th e pleading s an

devidenc e provide dherewit h(i.e. , Exhibit

A an d attachments thereto ) sho w tha t n o genuine issu e o f

materia l fac t exists . Therefore , Empir

e i s entitledt o adecisio na s amatte

r o f la w concerning th e existenc e o f aretur nto servic e entr

y i nthe aircraf t maintenanc e record s prior t o th e flight

onJune 1,2009 . Accordingly , Coun t III o f the Complain t concerning th e allege dviolatio no f Section s 91.405(b) , 91.407(a)(1) , and91.407(a)(2 ) must b e dismisseda s amatte

r o f law . Th e Complainan

t rest s uponth e mer

e allegation s of

it s pleading , without

settin g fort

h specific facts to show tha

t there i s agenuine issu e fo

r tria l concerning th e require dmaintenanc e recor dentrie s fo

r the retur nto servic e o f

N383CA prior

t o th e flight

o nJune 1,2009 . To th e

## contrary , Responden t provide s a

naffidavi t attachedheret

o fromChie

f Inspector Carmine J . Colaluc a(Exhibit

A) . Specifically , Chief

Inspector Colaluca' s unconteste dtestimon y establishe s tha t the necessar

y andrequire dmaintenanc e recor dentrie s fo

r th e retur nto servic e o f

N383CA existedprior

to th e flight

onJune 1,2009 . Accordingly , the unconteste devidenc e establishe s tha t ther e i s no genuine issu e a s to an y materia l fac t t o b e resolve dregardin g th e require dmaintenanc e recor dentr y fo r th e retur nto servic e of

N383CA prior

to th e flight

onJun e 1 , 2009 . Sinc e the Complainan

t ha s not an dcaimo t se t fort hspecific facts showing tha t ther e i s a genuine issue fo

r trial concerning th e allegedlack o f a"retur nt o service " maintenanc e recor dentry . Responden

t i s entitle dt o judgment

a s amatte r o f law . CONCLUSIO N Complainan

t ha s no t an dcannot se t fort hspecific facts showing tha t there i s agenuine issue fo r trial . WHEREFORE , Responden t respectfiill

y request s tha

t th e Honorabl e Ronni e A . Yoder , Chie f Adminisfrative La

w Judge , dismis s Coun

t II I of th e Complain

t regardin g 91.405(b) , 91.407(a)(1) , an

d91.407(a)(2 ) wit

hprejudice . Dated : Ma y 31,201 1 Respeo^:flb^ubmitted , JOR Y S . WJNTON , ESQ . 

## i e Aviatio nLa

w Fir m On e ffleseapenCourt , Suit

e 45 0 Rock^HeTMD 2085 0 Tel : (301 ) 294-855 0 Fax : (301 ) 294-252 5 Greg@AviationLawExperts.com Counsel fo r

Responden

t

# EXHIBI T A

## U . S . DEPARTMEN T O FTRANSPORTATION OFFICEO

FHEARINGS WASHINGTON , D.C . I NTH EMATTE RO F EMPIR EFLIGH T ACADEMY Responden

t FDM S NO . FAA-2010-029 0 HONORABL

ERONNI EA . YODE

R CHIE FADMINISTRATIV

ELA WJUDG E Hearing Date : NON

EASSIGNE

D Hearin g Location : NON

EASSIGNE

D AFFIDAVI T O FC . JOH NCOLALUCA , II I 1 . I hav e persona

l knowledg e o f

th e following facts andmak e th e following statement s unde r th e penalt y o f perjury , 2 . I hav e beenth e holder

o f a nAirfram e & Powerplan

t (A&P) mechani c certificat e sinc e 1972 . I hav e als o beenth e holde r of FA A Inspectio nAuthorizatio n(IA) fo r the pas t 3 0 years . 3 . I a mcurrently th e Chief

Inspector fo r aFA A CertifiedRepair

Station . 4 . I hav e beenrecognize da s a nexper t ingenera l aviatio nmaintenanc e b y th e Honorable Willia mE . Fowler , Jr. , Chief

Adminisfrative La

w Judge , th e Honorabl e Willia mR . Mullins , Administrativ e La w Judge , a s well a s the Nationa l Transportatio nSafet

y Board . 5 . I hav e reviewe dportion s o f th e FA A enforcemen

t investigativ e repor

t regardin g the above-referencedmatter . 6 . O no r about April 18,2009 , Paul Masaracchia , Airfram e & Powerplan

t (A&P) mechani c certificat e numbe r 104569374 , performeda10 0 hour inspection , includin g inspectio nof the landing gea

r o f N383CA , a

t a naircraf t tota l tachomete

r time o f 932. 1 hours . Se

e EXHIBI T 1 a t pag e 17 , item#28 .

## 7 . O

no r abou t Apri l 18 , 2009 , Paul Masaracchia , Airfram e & Powerplan

t (A&P) mechani c certificat e numbe r 104569374 , returne dthe aircraf t to servic e following th e 10 0 hou r inspectio na

t a naircraf t total tachomete

r time o f 932. 1 hours . Specifically , he determined tha t N383C A wa s "airworthy wit hrespec t t o it s maintenanc e condition. " Se e EXHIBI T 1 a t pag e 40 . 8 . O nor abou t Apri l 19 , 2009 , Paul Masaracchia , Airfram e & Powerplan

t (A&P) mechani c certificat e numbe r 104569374 , mad

e a naircraf t maintenanc e recor

dentr y andreturne d the aircraf t to service . Specifically , he statedtha t th e aircraf t wa s determine dt o be i

n "airworth y condition. " See EXHIBI T 2 . 9 . Thereafter , o nor

about Ma y 31,2009 , Same

r Elsayed , Airfram

e & Powerplan

t (A&P ) mechani c certificat

e numbe r 3245675 , returne dN383C A t o servic e following a5 0 hour inspectio na

t a naircraf t tota l tachomete

r time of 982. 2 hours . Specifically , Mr . Elsayed determinedth e aircraf

t to b e in"airworth

y condition. " See EXHIBIT 2 . 10 . Prior t o th e flight

onJun e 1,2009 , N383CA ha dbeeninspecte dandreturne dto servic e a s airworth y by Paul Masaracchia , Airfram e & Powerplan

t (A&P) mechani c certificat e numbe r 1045693744 , pursuant

to 1 4 C.F.R . §43.11 . See EXHIBIT S 1 & 2 . 11 . Prior t o th e flight

onJune 1 , 2009 , N383CA ha dbeeninspecte dandreturne dto servic e a s airworth y by Same r Elsayed , Airfram

e & Powerplan

t (A&P) mechani c certificat e numbe r 324567 5 pursuant

t o 1 4 C.F.R . §43.11 . Se

e EXHIBI T 2 . 12 . Basedupo nm

y education , fraining, andexperience , a s well a s m y investigatio no

f thi s matter , i t i s m y opinio nthat : Inaccordanc e wit

h1 4 C.F.R . § 91.405(b) , prior to the flight

onJun e 1 , 2009 , maintenanc e persoimel mad e appropriat

e entrie s inth e aircraf

t maintenanc e record s fo r N383CA , indicatin g th e aircraf t ha dbeenapprove dfo

r retur nt o service . I n accordanc e wit

h§ 91.407(a)(1) , prior

to th e flight

o nJune 1,2009 , N383CA ha dbeenapprove dfo

r retur nt o servic e by aperso nauthorize dunde r Section43. 7 o f th e Federa

l Aviatio nRegulations . I n accordanc e v^dt

h§ 91.407(a)(2) , prior

t o th e flight

o nJun e 1,2009 , th e maintenanc e recor

dentr y fo r N383C A require db y Section s 43. 9 or 43.11 , a s applicable , o f

the Federa

l AviationRegulation s ha

dbeenmade . 13. 1 a mcompeten

t to testif y a s to th e matter s statedherein . C^H NCOLALUCA , II I Dated : Ma y 27,201 1

# EXHIBIT 1

### DA20-C 1 AM M 

# Diamon d •/;•:-•::• > 

### Tim e Limit s an d Maintenanc e Clieck s IVIAINTENANC E PRACTICE S MAINTENANC E CHECKLIS TDA20-C 1 1 . Genera l Ente rth e applicabl e dat a i n th e block s below : S/ N Dat e 

# Cc Y

# >

A : 

# y r / Registratio n Engin e hours , TTSNrrSMO H Check : Airplan e Operatin g Hours . : . 

# ^ 1 \ ^ . 200 , 1000 , 6000 , iinnua l Inspection ) A t 2 5 hour s tim e sinc e ne wo f a n aircraft , inspec t th e item s i n th e 10 0 hou rcolum n tha t D O NO T hav e a n asteris k

(*) . Item s tha t d o hav e a n asterisk s besid e ma yb e initiale d "N/ A@ 2 5 hr " i n th e Initial s column . 2 . Preparatio n D o th e followin g item s befor e yo u star t th e applicabl e check : T Inspectio n Item s Interva l (Fligh t Hours ) ( . 5 0 / . 

# 7 ^ 

# Q -iai > 

# T T 20 0 100 0 600 0 Initials . Befor e yo u d o th e inspection : Rea d th e applicabl e Airworthines s Directives . Fo rairplane s tha t ar e no t U.S . Registered : Rea d th e applicabl e Servic e Bulletins . Examin e th e Lo g Books .

- D o a chec k

o f th e Technica l Records . Mak e sur e tha t th e mas s an d stati c momen t fo rth e ailerons , flaps , elevato r an d rudde rar e withi n th e specifie d limit s (Refe rt o Chapte r05-00 ) Clea n th e airplan e fully . (Refe rt o Chapte r12-30) . 

# (b

No t applicabl e at 2 5 hou rinspection . Doc#DA201.C 1 Rev . 1 3 

# 05-20-0 0 Pag e 5 3 0 Ap r200 8

### ../rSTS;. ^



## Tim e Limit s an d Maintenanc e Check s 

# Diamon d DA20-C 1 AM M 3 . Engin e Groun d Tes t D o a n engin e groun d tes t a s follow s (complet e a cop yo f th e Engin e Groun d Tes t Recor d a s part o f th e engin e groun d tes t (Refe rt o Paragrap h 7) .

Inspectio n Item s Interva l (Fligh t Hours ) 

### ^ m j 20 0 100 0 600 0 Initials . WARNING : D O NO TLE TPERSON S G O INT O TH E DANGE R ARE AO F TH E

PROPELLER . PROPELLER S CA N CAUS E INJUR YO R DEATH . WARNING : SE TTH E PARKIN G BRAK E T O ON . I F YO U D O NO TD O THIS , TH E

AIRPLAN E CA N MOVE . THI S CA N CAUS E INJUR YO R DEATH . 1 . 2 . 3 . 4 . D o a n operationa l tes t o f th e parkin g brake . Se t th e parkin g brak e t o ON . Pu t th e chock s agains t th e airplan e mai n wheels . D o a n engin e operationa l test .

- Fo rth e engin e ru n procedure s refe rt o theDA20-C 1 Fligh t Manual .

- Fo rth e operationa l tes t refe rt o TC M Maintenanc e Manua l Chapte r23 . Refe r t o th e operationa l checklis t (Pag e 3 ) fo r differenc e i n RP M settings .

- Recor d th e dat a i n th e checklis t i n 05-20 - 0 0 para.7 . Engin e Groun d Tes t Record . D o a n functiona l tes t o f th e fue l shut-of f valve , fo rcorrec t operation . (Refe rt o Chapte r28-20) . Whe n th e propelle rstop s rotating , se t th e ignitio n switc h t o th e OF F position . Se t th e maste rswitc h t o th e OF F position . An d se t th e fue l selecto rt o th e OF F position . 

# 0 X X X


# f ' X

x X

Pag e 6 3 0 Ap r200 8 

# 05-20-0 0 Doc#DA201-C 1 Rev . 1 3.\iw*ii*.;t».*>*J*^',i,'-^ i • iiii".Mj-'h...uAM.*a; . .i-t;>fc'.a^;>.i^j^h»Ui-.A>i.:*»ii^.i*i^<aa'^iiAiit>i/»ii»'i*>fc^ ^ *<wa i 

### ( • DA20.C 1 AM M 

# Diamond . Tim e Limit s an d Maintenanc e Checks
4 . Maintenanc e Checklis t Zone s D o th e applicabl e check s i n eac h o f th e zone s tha t follow : A . Engin e Compartment . Al l item s performed , th e findings , a s wel l a s thei rcorrectio n mus t b e recorde d i n accordanc e wit h a n approve d procedure s manual . Contac t Diamon d Aircraf t i f damage s ar e determine d whic h canno t b e repaire d i n accordanc e wit h a n approve d procedure s manual .

Inspectio n Item s Interva l (Fligh t Hours )



# C ^ 20 0 100 0 600 0 Initials . 

### WARNING : MAK E SUR E TH E EXHAUS T SYSTE M I S COO L BEFOR E YO U D O MAINTENANC E O NTH E ENGINE . TH E EXHAUS T SYSTE M CA N B E HOT . THI S CA

NCAUS E INJUR

Y T O PERSONS . 1 . Remov e th e to p an d botto m cowlings . Examin e th e cowlings . Mak e sur e tha t th e fastener s ar e serviceable . Loo k fo rcrack s an d area s tha t hav e go t to o hot . 

# T : (i > P- i WARNING : D O NO T GE TOI L O N YOU . OI L CA N CAUS E SKI N DISEASE . WARNING : D O NO T GE T FUE L O N YOU . FUE L CA N CAUS E SKI N DISEASE .

D O NO T ALLO W FIR E NEA R FUEL . FIR E BURN S AN D CA N CAUS E INJUR YT O PEOPL E AN D DAMAG E T O EQUIPMENT . 2 . 3 . Examin e th e engin e fo roil/fue l leaks . Remov e th e oi l drai n plug . Drain th e engin e oi l int o a n approve d containe r(wit h th e engine warm) .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r19 . Instal l th e drai n plug .

- Tighte n th e drai n plug . Torqu e t o 21.5 - 23. 8 N m (190-21 0 i n lbs) .

- Loc k th e drai n plu g wit h safet ywire . Replac e th e oi l filter . Refe rt o Chapte r79-00 . Examin e th e lubricatio n system .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r19 . 

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7 . Inspectio n Item s Cu t ope n th e use d oi l filter . Loo k fo r particle s o f metal . I f th e filte rcontain s particle s o f metal , refe rt o th e TC M Operator s Manual . Interva l (Fligh t Hours ) 5 0 10 0 

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X Initials . 

# } f ^ CAUTION : YO U MUS TUS E ENGIN E OIL S THA TAGRE E WIT H TH E APPLICABL E

REVISIO N O F TH E TELEDYN E CONTINENTA L MOTOR S (TCM ) SPECIFICATIO N MHS2 4 O R MHS27 . FO R MOR E INFORMATIO N SE E TC M SERVIC E BULLETI N M8 7 REVISIO N 1 O R TH E APPLICABL E REVISION . 8 .

10 .

11 .



### 12 . Fil l th e engin e wit h ne woil .

- Refe rt o th e TC M Maintenanc e Manua l fo roi l specification s an d quantity . Remov e th e spar k

plugs .

- Examin e th e spar k

plugs . Loo k especiall yfo rdamage d electrodes .

- Clea n th e spar k

plug s (refe rt o spar k plu g manufacturer s instructions) .

- D o a spar k

plu g ga p tes t (Refe rt o th e manufacturer s specifie d spar k plu g gap) . D o a compressio n tes t wit h th e engine war m an d th e throttl e open . Refe rt o TC M Maintenanc e Manua l Chapte r20 .

- D o th e compressio n tes t o n th e fou r cylinders . 

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Recor d th e compressio n tes t results . 

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plugs .

- Instal l th e spar k

plug s wit h a ne wgasket .

- Torqu e t o 33-4 0 N m (300-36 0 i n lbs) .

- Refe rt o Teledyn e Continenta l Motor s Servic e Instruction s fo rapprove d spar k plugs . D o th e 5 0 hou rignitio n syste m inspection .

- Refe rt o TC M Maintenanc e Manua l Chapte r12 . Pag e 8 3 0 Ap r200 8 

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14 . 15 . 16 . 

### 17 . 18 . 19 . D o th e 10 0 hou rignitio n syste m inspection .

- Refe rt o TC M Maintenanc e Manua l Chapte r12 . D o th e 5 0 hou rcylinde rassembl yinspection :

- Refe rt o th e TC M Maintenanc e Manua l Chapte r20 . D o th e 10 0 hou rcylinde rassembl y inspection :

- Refe rt o th e TC M Maintenanc e Manua l Chapte r20 . D o th e 5 0 hou raccessor ycas e inspection .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r18 . D o th e 10 0 hou raccessor ycas e inspection .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r18 . D o th e 5 0 hou rstarter/starte rdriv e inspection .

- Refe rt o th e TC M Maiptenanc e Manua l Chapte r17 . D o th e 10 0 hou rstarter/starte rdriv e inspection .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r17 . 

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- Refe rt o th e TC M Servic e Informatio n Directiv e SID97-3 C o rlates t approve d revisio n 20 . 21 . 22 . D o th e 5 0 hou rfue l injectio n syste m inspection .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r1 3 D o th e 10 0 hou rfue l injectio n syste m inspection .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r1 3 D o th e 5 0 hou rinductio n syste m inspection .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r14 . 

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\ 23 . 24 . 25 . 26 . 27 . 

# \o n a . DA20-C 1 AM M Interva l (Fligh t Hours ) Inspectio n Item s Q^ ^ D o th e 10 0 hou rinductio n syste m inspection .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r14 , D o th e 5 0 hou rcrankcas e inspection . i

- Refe rt o th e TC M Maintenanc e Manua l Chapte r21 . D o th e 10 0 hou rcrankcas e inspection .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r21 . 1 D o th e 5 0 hou rengin e driv e trai n inspection .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r22 . D o th e 10 0 hou rengin e driv e trai n inspection .

- Refe rt o th e TC M Maintenanc e Manua l Chapte r22 . , (
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29 .

Pag e 3 0 A 1 Examin e th e exhaus t system . Loo k especiall yfo rcrack s an d hea t damage .

- Remov e th e flexibl e hose s fro m th e hea t exchanger .

- Remov e th e hea t exchange rshroud .

- D o a chec k

o f th e muffler . Loo k especiall yfo rcrack s an d leakage .

- Instal l th e hea t exchange rshroud .

- Instal l th e flexibl e hose s t o th e hea t exchanger .

- Refe rt o Chapte r78-00 . Examin e th e cabi n hea t system .

- Remov e th e wor m driv e clam p fro m th e flexibl e hos e a t th e cabin-hea t selector valve .

- Disconnec t th e flexibl e hos e fro m th e cabin-hea t selector-valve .

- Examin e th e flexibl e hos e fo rdamage . 

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30 . 31 . 32 . 33 . 34 . 35 . 36 . 37 . 38 . 39 . 40 . 41 . 42 . 43 . - Examin e th e cabin-hea t selector-valve .

- Connec t th e flexibl e hos e t o th e cabin hea t selector-valve .

- Instal l th e wor m driv e clamp . Examin e th e engin e baffles . Loo k especiall y fo rcrack s an d correc t attachment . Examin e th e cowlin g sea l o n th e firewal l extension . Examin e th e electrica l connection s o n th e generator . Examin e th e generato rmountin g bracket . Loo k especiall yfo rcracks , th e conditio n o f th e mountin g bolt s an d th e correc t attachmen t o f th e mountin g bolts . D o a tes t fo rcorrec t adjustmen t o f th e generato rbelt . Refe rt o Chapte r24-30 . Examin e th e ai rhoses . Loo k especiall yfo r sign s o f leakag e an d damage . Mak e sur e th e ai rhose s ar e correctl yattached . Examin e th e cabl e tie s an d al l electrica l connectors . Pul l lightl yt o mak e sur e the y ar e no t loos e Examin e th e batter yare a (aircraf t wit h fron t mounte d batter yonly) . Loo k especiall yfo r cleanliness . Tes t startin g vibrato rbatter y(Refe rt o Chapte r74-00) . Examin e th e drai n pipes . Loo k especiall yfo r sign s o f chafin g an d damage . Mak e sur e th e drai n pipe s ar e clear . Examin e th e fue l hoses . Loo k especiall yfo r sign s o f leakag e an d damage . Mak e sur e th e fue l hose s ar e correctl yattached . Examin e th e oi l cooler . Loo k especiall yfo r leakag e an d damage . Mak e sur e th e coolin g fin s ar e no t blocked . Replac e th e ai rfilter .

- Refe rt o Chapte r71-60 . Examin e th e ai rfilte r -Refe rt o Chapte r71-60 . 

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Inspectio n Item s Interva l (Fligh t Hours ) ^ 20 0 100 0 600 0 Initials . 44 , 45 . 46 .

47 . 48 . 49 . 

### 50 . 51 .

52 .
53 , Examin e th e ai rbo x

- Refe rt o Chapte r71-60 . Examin e th e engin e starte rrelay . Loo k especiall yfo rcorrec t attachment . Examin e th e throttl e an d mixtur e controls .

- Mak e sur e tha t th e connectio n t o th e contro l leve ri s tight .

- Mak e sur e tha t th e en d fittin g ca n tur n i n th e contro l lever .

- Examin e th e oute rcables . Loo k especiall yfo rwea ran d fo rkinks .

- O n aircraf t wit h a standar d fue l pum p only , lubricat e th e mixtur e contro l inne r cabl e wit h a smal l amoun t of oil . Refe r t o Chapte r12-20 . Clea n th e engin e an d engin e compartment .

- Refe rt o Chapte r12-30 . Mak e sur e ther e i s n o blockag e o f th e engin e oi l separator . Lon g operatio n of th e engine a t lo wtemperatur e wit h hig h ai r humidity , ca n caus e blockag e o f th e breathe r pipe . Remov e an d replac e th e engin e moun t hardwar e o n th e firewall . Replac e al l o f th e engin e moun t bolts . Examin e th e engin e mount s no t replaced . Loo k especiall yfor :

- Crack s o rcorrosion .

- Correc t attachmen t an d conditio n o f th e mountin g bolts .

- Deterioratio n o f th e shoc k mounts .

- Correc t torqu e valu e (Refe rt o Chapte r 20-00 , Sectio n 4) . Visuall yexamin e th e forwar d firewall . Examin e th e conditio n o f th e past e fille t an d fir e pain t ove rth e edg e o f th e fir e shiel d o n th e fron t fac e o f th e firewall . Chec k fo r cracks , damag e an d disbon d fro m th e fir e shield . Blee d th e fue l system . (Refe rt o Chapte r73-00) . 

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inspectio n Item s Interva l (Fligh t Hours ) 20 0 100 0 600 0 

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1O-240- B engin e installe d i n th e DA20-C 1 i s 100 0 ±2 5 RPM .

- Refe rt o th e TC M Servic e Informatio n Directiv e S1D97-3 C o rlate rapprove d revision . 54 . D o th e fue l syste m check/adjustment . Refe rt o th e TC M Maintenanc e Manua l warnin g Chapte r6 . 

# D Th WARNING : D O NO TLE TPERSON S G O INT O TH E DANGE R ARE AO F TH E

PROPELLER . PROPELLER S CA N CAUS E INJUR YO R DEATH . WARNING : YO U MUS TMAK E SUR E THA TTH E ENGIN E I S SAF E BEFOR E

YO U TUR N TH E PROPELLER . DISCONNEC TTH E SPAR KPLU G LEADS . MAK E SUR E THAT :

- TH E IGNITIO N SWITC H I S I N TH E "OFF " POSITION .
- TH E "P " LEAD S AR E GROUNDED .

- TH E THROTTL E I S SE TT O "CLOSED" .

- TH E MIXTUR E CONTRO L I S SE TT O "LEA N CUT-OFF" . WARNING : FAILUR E T O COMPL YWIT H TH E FOLLOWIN G MA YRESUL TI N

TH E LOS S O F TH E PROPELLER I TH E HU B O F AWOODE N PROPELLE R WIL L SHRIN KO R EXPAN D T O MATC H TH E AMBIEN T CONDITIONS . EXCESSIV E HU B SHRINKAGE , EESPECIALL Y POSSIBL E DURIN G VER YCOL D AND/O R DR YAMBIEN T CONDITION S CA N RESUL TI N LOS S O F PROPELLE R BOL T TORQU E (PRE-LOAD) . THI S CA N ALLO W SLIGH TMOVEMEN T RELATIV E T O TH E DRIV E FLANGE , WHIC H MA YRESUL TI N DAMAG E T O TH E PROPELLE R AND/O R TH E PROPELLE R BOLTS , POSSIBL YEVE N LOS S O F TH E PROPELLER I T O PREVEN TTHIS . PROPE R INSTALLATIO N AN D PERIODI C RE-TORQUIN G I N ACCORDANC E WIT H AL L APPLICABL E MAINTENANC E INSTRUCTION S I S NECESSARY . UNDE R AL L CIRCUMSTANCE S TH E INSPECTIO N INTERVAL S MUS TNEVE R EXCEE D 5 0 HOURS . EXTREM E CHANGE S I N AMBIEN TCONDITION S (TEMPERATURE/HUMIDITY ) MA Y REQUIR E SHORTE R INSPECTIO N INTERVALS . 55 .
56 . Remov e an d clea n th e spinner . Examin e th e spinne ran d backin g plat e fo rcracks . Fo r Sensenic h propelle rW69EK-6 3 (3/8 " bol t attachment ) only .

- Refe rt o Chapte r51 . Examin e th e propelle rextension . Inspec t fo r cracks , dent s an d wea rdamage . Mak e sur e tha t i t i s seate d correctly . 

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57 ,

58 . Inspectio n Item s

59 . Chec k

propelle rattachmen t bol t torques . Refe rt o Chapte r61 . Fo rSensenic h propelle rW69EK7 - 6 3 o rW69EK7-63 G (7/16 " bol t attachment ) refe rt o th e Sensenic h W69EK7-C F Manual . Fo rSensenic h propelle rW69EK-6 3 (3/8 " bol t attachment ) refe rt o th e Sensenic h W69EK-C F Manual . Fo rHoffman n propelle rHO-14HM-175 - 15 7 Refe rt o th e Hoffman n Owner' s Manua l numbe rE0110.74 . Interva l (Fligh t Hours ) 

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CAUTION : IMPROPE R TORQU E VALUE S WIL L B E OBTAINE D B YMEASURIN G TH E BREAKIN G TORQU E I N ALOOSENIN G DIRECTION . TH E TORQU E SHOUL D B E CHECKE D I N ATIGHTENIN G DIRECTIO N AN D ADJUSTE D A S NEEDED .

60 . 

### 5 1 Chec k

blad e tracking . Trackin g mus t no t excee d 1/8" .

- Refe rt o th e Sensenic h Documen t (W69EK-C F o rW69EK7-CF )

- Refe rt o Th e Hoffman n propelle r Owner' s Manua l (numbe rE 0110.74) . Instal l ne wcotte rpin s (W69EK7-6 3 o r W69EK7-63 G propelle rwit h castellate d nut s only) . Lockwir e th e attachmen t bolt s i n pair s (Hoffman n an d W69EK-6 3 propeller ) Instal l th e spinner .

- Refe rt o Chapte r61 . Sensenic h propelle ronly : Appl ya non-silico n automotiv e typ e past e wa xt o th e propelle rblades . ^ ; 

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s
B . Fron t Fuselag e Al l item s performed , th e findings , a s wel l a s thei rcorrectio n mus t b e recorde d i n accordanc e wit h a n approve d procedure s manual . Contac t Diamon d Aircraf t i f damage s ar e determine d whic h canno t b e repaire d i n accordanc e wit h a n approve d procedure s manual .

Inspectio n Item s Interva l (Fligh t Hours ) ( M ) 

### ^ 20 0 100 0 600 0 Initials .

3 . Examin e th e complet e surfac e o f th e fron t fuselage . Loo k

especiall yfo rdamag e (dents , cracks , holes , scratche s an d delamination) . Examin e th e pain t coat . Visuall yexamin e th e conditio n o f th e paint . Loo k fo rchips , scratches , U V damage , an d conditio n o f fire-proo f pain t aft o f lowe rcow l outlet . Inspec t fo rcrack s i n th e pain t a t th e bondin g sea m dow n th e centr e lin e o f th e fuselage , uppe ran d lowe rsurfaces . D o a visua l inspectio n an d a ta p tes t o f th e fuselag e skin .

- Inspec t fo rdisbondin g betwee n interna l composit e component s an d skin . Examin e th e composit e structur e aroun d th e entranc e steps . Inspec t especiall yfo rcrack s o rdelamination s i n th e attachmen t area . Examin e th e canopy . Chec k th e latchin g component s fo rcorrosio n wea ran d damage .

- Inspec t th e af t moun t an d rea rhinge , th e forwar d attachin g points , th e rubbe r stoppe ran d th e balanc e spring . Mak e sur e th e canop ylockin g mechanis m wil l release . (Refe rt o Chapte r52-10) . Visuall yexamin e th e canop yframe . Chec k fo rdelamination . scratche s an d cracks , especiall yaroun d th e fastene rholes . D o th e canop ylatc h forc e test . (Refe rt o Chapte r52-10) . Examin e th e fuselag e aroun d th e mountin g hardwar e fo rth e canop ylatch .

- Inspec t fo rsecurit yo f th e mountin g hardware . 

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## Tim e Limit s an d Maintenanc e Check s 

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### 100 0 600 0 Initials . 9 . 10 . 11 . 12 . 13 . 14 . 15 . 16 . 17 . 18 . 19 . 20 . 21 . 22 . 23 . - Inspec t fo rcrack s an d delaminatio n o f th e composite . Remov e th e whee l fairings . Loo k fo rcrack s o n th e fairin g mounts . (Refe rt o Chapte r32-40) . Lif t th e airplan e o n jacks . (Refe rt o Chapte r07-10) . Examin e th e tires . Loo k especiall yfo rcut s an d wear . Measur e th e tir e pressure . (Refe rt o Chapte r12-10) . Examin e th e rim s o f th e mai n an d th e nose wheel . Loo k

especiall yfo rcracks . Examin e th e whee l bearings . Loo k especiall yfo rplay , corrosio n an d irregula r operation . Remov e th e mai n wheels . Clea n an d lubricat e th e bearings . (Refe rt o Chapte r12-20) . Visuall yexamin e th e conditio n o f th e axles . Loo k especiall yfo rcrack s an d corrosion . Visuall yexamin e th e strut s an d shim s i n th e outboar d brackets . Chec k fo rth e correc t fi t of th e components . Remove , disassembl e an d clea n th e brak e cylinder s (4x ) an d caliper s (2x) . Replac e th e O-Ring s an d assembl e th e brak e cylindei- s (4x ) an d caliper s (2x) . Examin e th e brak e lining . Loo k especiall y fo rwear. Minimu m thicknes s 3. 0 m m (0.1 2 in ) Examin e th e brak e disks . Loo k especiall y fo rwear. Minimu m thicknes s 3. 8 m m (0.1 5 in ) Instal l th e mai n wheels . (Refe rt o Chapte r32-40) , Remov e th e mai n landing-gea rstrut s (Refe rt o Chapte r32-10) , Examin e th e mai n landin g gear ,

- Inspec t fo rcrack s an d deformation ,

- Inspec t th e stru t fo rdistortion , corrosio n an d pain t condition . Pag e 1 6 3 0 Ap r200 8 

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Inspectio n Item s 24 . Measur e th e maximu m deflectio n o f th e mai n landing-gea rstruts . La ya straigh t ro d o n th e uppe rsid e o f th e stru t an d measur e th e maximu m valu e o f th e gap -

- U p t o 3 mm : Chec k

th e mai n gea rfo r corrosio n an d crack s (particularl ya t th e (0.1 2 in ) curvatures )

- Mor e tha n 3 m m (0.1 2 in ) gap : Replac e th e strut . 25 . Replac e al l o f th e aircraf t attachmen t hardwar e t o th e mai n landin g gear . 26 . Instal l th e mai n landing-gea rstrut s (Refe rt o Chapte r32-10) . 27 . D o a tes t fo rtoe-i n an d camber . (Refe rt o Chapte r32-10) . 28 . Examin e th e nose-whee l assembly . Loo k especiall yfo rcorrec t attachment , crack s an d deformation . 29 . Remov e th e nos e landing-gea rstru t (Refe rt o Chapte r32-20) . 30 . Visuall yexamin e th e NL G stru t condition . Loo k especiall yfo rdistortion , corrosio n an d conditio n o f th e paint . 31 . Visuall yexamin e th e NL G stru t pivots .

- Loo k especiall yfo rcrack s i n th e radiu s o f th e assembly , corrosio n an d wear . An y corrosio n need s t o b e assessed , treate d and/o rth e componen t replaced .

- Inspec t th e thread s o f th e lowe ren d o f th e stru t fo rcracks . 32 . Visuall yexamin e th e NL G stru t uppe rattac h bolt . Loo k

especiall yfo rcrack s an d corrosion . 33 . D o a visua l inspectio n o f th e NL G bushing s i n th e T-pane l o n th e botto m o f fuselage .

- Chec k fo rth e securit yo f th e bushin g i n th e T-panel .

- D o a ta p tes t t o chec k fo rth e conditio n of th e surroundin g laminate .

- Chec k th e bon d o f th e T-pane l t o th e floo rpane l an d t o th e fuselag e skin , Doc#DA201-C 1 Rev . 1 3 

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### Initials . 34 . 35 . 36 . 37 . 38 . 39 . 40 .
41 . 42 . 43 . 44 . Examin e th e nose-gea rjournal-bearing s i n th e botto m o f th e fuselage . Loo k especiall y fo rplay . Examin e th e journa l i n th e elastomeri c spring . Loo k

especiall yfo rplay . Examin e th e elastomeri cspring . Loo k especiall yfo rdamag e an d tighte n i f necessary . Replac e th e nos e landin g gea relastome r packag e (Refe rt o Chapte r32-20) . Chec k th e telescopi cro d fo rcorrosio n an d excessiv e wear . Visuall yexamin e th e NL G fork . Loo k especiall yfo rcrack s an d corrosion . Instal l th e nos e landing-gea rstru t (Refe rt o Chapte r32-20) . Examin e th e nose-whee l fork . D o a tes t fo r pla yan d caste rfriction . (Refe rt o Chapte r32-20) . Th e frictio n shoul d b e 3 - 5 N (6.7 5 - 11.25lbs)attheaxle . Lubricat e th e spherica l bearin g at th e to p o f th e elastomeri cspring . (Refe rt o Chapte r12-20) . Lowe rth e airplan e of f jacks . (Refe rt o Chapte r07-10) . Instal l th e whee l fairings . Examin e th e exterio rplacards . Mak e sur e tha t the yar e no t damage d an d tha t non e ar e missing . Replac e an ytha t ar e damage d o rmissing . (Refe rt o Chapte r11-20) . 

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# Diamond . Tim e Limit s an d Maintenanc e Check s C . Cockpit Al l item s performed , th e findings , a s wel l a s thei rcorrectio n mus t b e recorde d i n accordanc e wit h a n approve d procedure s manual . Contac t Diamon d Aircraf t i f damage s ar e determine d whic h canno t b e repaire d i n accordanc e wit h a n approve d procedure s manual .

Inspectio n Item s Interva l (Fligh t Hours ) 

# w 109 ^ 

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10 . Remov e th e sea t shells . (Refe rt o Chapte r25-10) . Visuall yexamin e th e seat s an d sea t attachments . Loo k

especiall yfo rcracks , delaminatio n an d damag e aroun d th e fastenerholes . Visuall yexamin e th e cockpi t floor . Loo k especiall yfo rcrack s o rdelaminatio n aroun d th e aft rudde rpeda l bracket , boardin g step , an d th e throttl e quadran t opening . Examin e th e safet ybelt s fo rgenera l conditio n an d securit yo f th e meta l fittin g i n th e surroundin g composite . Mak e sur e th e loc k

mechanis m operate s correctly .

- Insert th e connecto rint o th e buckj e an d pul l o n th e connector . Mak e sur e th e ratche t hold s th e connector . Th e connecto rmus t fal l freel yfro m buckl e whe n hel d i n a vertica l positio n an d whe n yo u ope n th e cove rt o th e releas e position . Examin e th e cabl e tie s an d electrica l connectors . Pul l lightl yt o mak e sur e the y ar e no t loos e Examin e th e contro l sticks . Mak e sur e tha t th e contro l stic k

attachment s ar e no t loos e an d d o no t catch . Examin e th e contro l stic k stops . Examin e th e pitot-stati csyste m wate rtraps . Examin e th e stal l warnin g hose . Loo k especiall yfo rcontaminatio n b ywater . (Refe rt o Chapte r34-20) . Examin e th e flap-actuato rindicato ran d positio n switches . Loo k especiall yfo r correc t attachmen t an d operation . Doc#DA201-C 1 Rev . 1 3 

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11 .
12 .
13 . 14 .



### 15 . 16 . 

### 17 . 18 . 19 . 20 . Inspectio n Item s Interva l (Fligh t Hours )



# r ; 50 ^ Examin e th e flap-actuato rstop s an d support . Loo k especiall yfo rcorrec t attachment . Examin e fo rsecurit yo f th e bracke t o n th e laminat e an d crack s i n th e surroundin g laminate . Examin e th e locking-devic e fo rth e win g main-bolt . Loo k

especiall yfor :

- Correc t operation .

- Condition . Examin e th e mountin g fo rth e landin g gear . Loo k especiall yfo rcorrec t attachmen t an d loc k devices . Visuall yexamin e th e ML G an d A-bol t attachmen t brackets . Loo k especiall yfor :

- Crack s in , o rcorrosio n o f th e bracket .

- Disbon d fro m th e laminate .

- Delaminatio n i n th e surroundin g laminate . Examin e th e rudde rpedals . Loo k especiall y fo rcorrec t attachmen t an d function . (Refe rt o Chapte r27-20 ) Examin e th e rudde rcable s an d pulleys . Loo k especiall yfo rcorrec t attachmen t an d function , an d fo rwear , damag e an d corrosion . (Refe rt o Chapte r27-20 ) Examin e th e area s wher e th e rudde rcabl e pulley-bracket s attac h t o th e fuselage . Loo k especiall yfo rsecurit yo f th e pulle ybracket s o n th e laminat e an d crack s i n th e surroundin g laminate . Examin e th e brak e pipes/hose s an d components . Loo k

especiall yfo rleakage . Drai n an d replac e th e brak e flui d i n th e brak e reservoirs . (Refe rt o Chapte r32-40 ) Examin e th e brak e reservoir s o n th e co-pilot s side . Mak e sur e th e flui d leve l i s correct . Th e flui d leve l mus t b e 12m m t o 25m m (1/2 t o 1 in ) belo wth e to p fac e o f th e reservoi rfille rhole . Pag e 2 0 3 0 Ap r200 3 

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# (5 ^ 100 , 20 0 100 0 600 0 Initials . ^ 21 . Examin e th e instruments . Mak e sur e that :

- Th e marking s ar e clear .

- Th e functio n i s correct .

- Switche s ar e correctl yattached . 22 . Examin e th e interio rplacards . Mak e sur e tha t the yar e no t damage d an d tha t non e ar e missing . Replac e an ytha t ar e damage d o rmissing . (Refe rt o Chapte r11-30) . 23 . Remov e th e instrumen t pane l cover . 24 . Remov e th e instrumen t panel . (Refe rt o Chapte r31-10) . 25 . Remov e th e cove rbo xfo racces s t o th e fue l shut-of f valve . (Refe rt o Chapte r28-20) . 25 . Examin e th e tw o fue l hose s tha t ru n fro m th e drai n tra p block , alon g th e floo ro f th e cockpi t t o th e fue l shut-of f valve , a s follows : NOTE : Yo u mus t blee d th e engin e fue l syste m afte ran ywor k whic h allow s ai rint o th e airplan e fue l suppl y system . Refe rt o Chapte r73-0 0 fo r th e blee d procedure .

- Disconnec t th e fue l hose s fro m th e fue l shut-of f valve .

- Disconnec t th e othe rend s o f th e tw o fue l hose s fro m th e maintenanc e drain-ta p block .

- Pul l th e tw o fue l hose s ou t fro m th e fue l hos e condui t tha t run s alon g th e floor . NOTE : Ti e a satisfactor ycor d t o on e en d o f eac h fue l hos e s o tha t the ypul l throug h whe n eac h hos e i s removed . Thi s wil l assis t wit h th e installatio n o f th e hos e i n th e conduit . Visuall yinspec t th e tw o fue l hose s fo r damage , sign s o f wear , fue l seepag e an d discoloration . Mak e sur e tha t eac h hos e an d th e connector s ar e i n a full ysatisfactor y condition . Replac e a hos e tha t yo u fin d t o b e no t satisfactory , Doc#DA201-C 1 Rev . 1 3 

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# 5 50 > 

# "K;; ^ 8 9 20 0 100 0 600 0 

### Initials .

27 . 28 . 

### 29 .

30 . 31 . 32 .
33 . - Pu t th e tw o fue l hose s bac k throug h th e conduit . Us e th e cord s t o hel p i n routin g th e hose s through . Remov e an d discar d th e cords .

- Connec t th e fue l hose s t o th e maintenanc e drain-ta p block .

- Connec t th e tw o fue l hose s t o th e fue l shut-of f valve . Visuall yexamin e th e fue l shut-of f valve . Loo k especiall yfo rsign s o f corrosion , leakag e an d damage . Mak e sur e tha t i t i s correctl yattache d t o th e firewall . Mak e sur e tha t th e fue l hose s ar e correctl yattached . Instal l th e cove rbo xtha t fit s ove rth e fue l shut-of f valve . (Refe rt o Chapte r28-20) . Visuall yexamin e th e firewall . Inspec t th e conditio n o f th e laminat e whe n viewe d fro m th e cockpi t sid e fo rcracks , discoloratio n an d delamination . Particularl yaroun d th e engin e moun t fastene rhole s an d th e batterybox . Examin e th e structur e fo rsecurit yo f th e attachin g bolt s o n th e firewal l an d crack s i n th e surroundin g laminate . Visuall yexamin e th e cabi n hea t valv e an d cabi n ai rducts . Mak e sur e tha t the yar e no t damage d an d ar e correctl yattached . Instal l th e instrumen t panel . (Refe rt o Chapte r31-10) . Visuall yexamin e th e cockpi t are a fo ran y sign s o f fue l leaks . Follo walon g th e fue l hos e condui t an d fue l hose s fro m th e drai n tra p block , alon g th e floo ro f th e cockpi t t o th e fue l shut-of f valve . Mak e sur e tha t ther e ar e n o sign s o f fue l leaks . Examin e th e instrumen t panel . Mak e sur e that :

- Wirin g i s correctl yattached .

- Instrument s ar e correctl yattached .

- Hose s ar e correctl yattached .

- Circui t breaker s ar e correctl yattached . Pag e 2 2 3 0 Ap r200 8 

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35 .

36 .
37 . 38 . Interva l (Fligh t Hours )

Inspectio n Item s . 50_ y Examin e th e Vacuu m inle t filter . (Aircraf t wit h pneumati cinstrumen t syste m only ) Mak e sur e that :

- Th e filte ri s correctl yattached .

- Th e filte ri s clean .

- Replac e th e filte ra t 50 0 h rintervals . Examin e th e Vacuu m syste m regulator . (Aircraf t wit h pneumati cinstrumen t syste m only ) Mak e sur e that :

- Th e regulato ri s correctl yattached . <100" ,



# 0 ( y

- Replac e th e filter . Lubricat e th e ignitio n switch :

- Se e FA AA D 93-05-0 6 referenc e ACS/Gerde s servic e bulleti n SB92-01 - ACS , ignitio n switc h lubrication/inspection . Instal l th e instrumen t pane l cover . Examin e th e compass . Mak e sur e that :

- Th e compas s i s correctl yattached .

- Th e flui d leve l i s correct . 

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D . Cente rFuselage , Interna l Al l item s performed , th e findings , a s wel l a s thei rcorrectio n mus t b e recorde d i n accordanc e wit h a n approve d procedure s manual . Contac t Diamon d Aircraf t i f damage s ar e determine d whic h canno t b e repaire d i n accordanc e wit h a n approve d procedure s manual .

Inspectio n Item s 

### ' ^ Interva l (Fligh t Hours ) 20 0 100 0 600 0 Initials .

7 . 8 , 9 ,

10 . Examin e th e fir e extinguisher . Mak e sur e th e fir e extinguishe rwil l release . An d mak e sur e th e fir e extinguishe rcontent s ar e full . D o a chec k

o f th e extinguishe rexpirydate . (Refe rt o Chapte r26-00) . Examin e th e baggag e net . Mak e sur e th e sprin g clip s operat e correctly . Examin e th e are a wher e th e baggag e ne t hook s attac h t o th e fuselag e side . Inspec t th e composit e fo rsecurit yo f th e hook s an d delamination . Examin e th e ELT . (Refe rt o Chapte r25-60) . D o a batterychec k

(Refe rt o Chapte r24-31) . Loo k especiall yfor :

- Charg e an d capacity .

- Correc t aci d level .

- Correc t mounting . Examin e th e batter yba yare a (aircraf t wit h aft mounte d batter yonly) . Loo k especiall y fo rcleanliness . Remov e th e cente rfuselag e panel s o n th e botto m o f th e airplan e fo raccess . Remov e th e baggag e compartmen t floo rfo r access . (Refe rt o Chapte r25-10) . Remov e th e batter yan d batter ytra y(o n aircraf t wit h th e af t mounte d batteryonly ) fo r access . (Refe rt o Chapte r24-31) . Visuall yexamin e th e interio ro f th e tai l section . Loo k

especiall yfo rsign s o f damag e (dents , scratches , cracks , hole s an d delamination) . Examin e th e pus h ro d guide s fo rth e elevato r push-rod . Loo k

especiall yfo rcorrec t attachmen t an d freedo m o f movement . Pag e 2 4 3 0 Ap r200 8 

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# 'fi n 11 . 12 . 

### 13 . 14 . 

### 15 . Examin e th e fla p contro l mechanis m o n th e af t contro l bulkhead . Loo k especiall yfo r damage , corrosion , correc t attachmen t an d loc k devices . Examin e th e ailero n contro l syste m o n th e aft contro l bulkhead . Loo k especiall yfo r wear , damage , corrosion , correc t attachmen t an d loc k devices . D o a cabl e tensio n tes t o f th e rudde rcontro l cable . (Refe rt o Chapte r27-20) . Examin e th e rudde rcontro l leve ran d cable s o n th e B-bulkhead . Loo k especiall yfo r damage , corrosion , correc t attachmen t an d loc k devices . Examin e th e rudde rcontro l cable s i n th e cente rfuselage . Loo k especiall yfo rwear , damage , corrosio n an d correc t loc k devices . WARNING : D O NO TGE TFUE L O N YOU . FUE L CA N CAUS E SKI N DISEASE .

D O NO TALLO W FIR E NEA R FUEL . FIR E BURN S AN D CA N CAUS E INJUR YT O PEOPL E AN D DAMAG E T O EQUIPMENT . 16 . Defue l th e fue l tank . (Refe rt o Chapte r12-10) . 17 . Remov e th e fue l tank . Loo k fo rcorrosio n an d damage . (Refe rt o Chapte r28-10) . 18 . Remov e an d clea n th e gascolato rfilte rbowl . Instal l th e gascolato rfilte rbowl . (Refe rt o Chapte r28-20) . 19 . Examin e th e fue l tan k strap . Loo k

especiall y fo rru b marks . 20 . Examin e th e fue l tan k an d fue l pipe s fo r leakage . 21 . Examin e th e fue l syste m electrica l cable s an d groun d strap . Loo k especiall yfo rru b marks . 22 . Examin e th e fille rnec k o f th e fue l tan k

an d th e fille rcap . Loo k

especiall yfo rfue l leak s an d damage . 23 . Examin e th e fue l ven t pipe . Loo k especiall y fo rru b mark s an d damage . Mak e sur e th e ven t pip e i s clear . Doc#DA201-C 1 

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### 100 . 20 0 

### 100 0 600 0 Initials . 24 . 25 . 26 . 27 . 28 . 29 .
30 . Examin e th e cabl e tie s an d electrica l connectors . Pul l lightl yt o mak e sur e the y ar e no t loose . Visuall yexamin e th e B-bulkhead . Loo k fo r crack s an d delamination , especiall yaroun d th e fue l tan k

attachments . Visuall yexamin e th e rudde rleve rmountin g unde rth e B-bulkhead . Examin e fo rsecurit y of th e bracke t o n th e laminate , elongatio n o f hole s an d crack s i n th e surroundin g laminate . Examin e th e rolle rguide s fo rth e rudde r contro l cable s i n th e centr e fuselage . Loo k especiall yfo rdamage , pla yan d excessiv e wear. Instal l th e batter yan d batter ytray . O n aircraf t wit h a n af t mounte d batteryonly . (Refe rt o Chapte r24-31) . Instal l th e fue l tank . (Refe rt o Chapte r28-10) . D o a calibratio n tes t o f th e fue l quantit y indicatio n system . (Refe rt o Chapte r28-00) . Instal l th e botto m cente rfuselag e panels . 

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# c Tim e Limit s an d Maintenanc e Check s E . Rea rFuselag e Al l item s performed , th e findings , a s wel l a s thei rcorrectio n mus t b e recorde d i n accordanc e wit h a n approve d procedure s manual . Contac t Diamon d Aircraf t i f damage s ar e determine d whic h canno t b e repaire d i n accordanc e wit h a n approve d procedure s manual .



### Inspectio n Item s Interva l (Fligh t Hours )



# (3° ; Examin e th e complet e surfac e of th e rea r fuselage . Loo k

especiall yfo rdamag e (dents , cracks , holes , scratche s an d delamination) . O n aircraf t wit h a rea rwindow , examin e around th e insid e an d outsid e o f th e window . Inspec t th e structur e an d th e seal . Loo k especiall yfo rdelaminatio n of th e structur e an d leak s o rbreak s i n th e windo wseal . Visuall yexamin e th e conditio n o f th e paint . Loo k fo rchips , scratches , U V damage. D o a visua l inspectio n an d a ta p tes t o f th e fuselag e skin .

- Inspec t fo rdisbondin g betwee n interna l composit e component s an d skin . Examin e th e pus h ro d guide s fo rth e elevato r push-rod . Loo k

especiall yfo rcorrec t attachment . An d freedo m o f movement . Examin e th e rudder-contro l cable s an d turnbuckles . Loo k

especiall yfo rwear , damage , corrosio n an d correc t loc k devices . 

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# Diamond . DA20-C 1 AM M F . Tai l Al l item s performed , th e findings , a s wel l a s thei rcorrectio n mus t b e recorde d i n accordanc e wit h a n approve d procedure s manual . Contac t Diamon d Aircraf t i f damage s ar e determine d whic h canno t b e repaire d i n accordanc e wit h a n approve d procedure s manual .

Inspectio n Item s Interva l (Fligh t Hours ) ( ^ 20 0 100 0 600 0 Initials .

6 . 7 , Examin e th e complet e surfac e o f th e aft part o f th e fuselage , vertica l stabilizer , an d horizonta l stabilizer . Loo k especiall yfo r damag e (dents , cracks , holes , scratche s an d delamination) . Loo k

especiall yaroun d th e acces s panels . D o a visua l inspectio n an d a ta p tes t o f th e vertica l stabilize ran d horizonta l stabilizer .

- Inspec t fo rdisbondin g betwee n interna l composit e component s an d th e skin .

- Inspec t fo rdisbondin g betwee n th e trailin g edg e an d th e skin . D o a visua l inspectio n an d atap-fes t o f th e leadin g edg e o f th e horizonta l stabilizer . Examin e fo rdisbond s an d crack s abov e o r belo wth e overta p seam . Visuall yexamin e th e forwar d mountin g bracke t o f th e horizonta l stabilizer . Loo k especiall yfor :

- Crack s i n th e bon d t o th e plate .

- Delaminatio n i n th e ri b aroun d th e ' . fasteners .

- Th e conditio n o f th e spherica l bearing .

- Th e fi t o f th e pi n i n th e bearing . Visuall yexamin e th e drai n hole s i n th e horizonta l stabilizer . Mak e sur e tha t the yar e open . Visuall yexamin e th e conditio n o f th e paint . Loo k fo rchips , scratches , U V damage . Examin e th e lowe rfin . Loo k especiall yfo r damag e t o th e botto m o f th e fi n an d correc t attachment . D o a visua l inspectio n an d a ta p test . Inspec t th e fuselag e ski n aroun d th e lowe r tai l fi n fo rcracks . Inspec t bon d lin e t o vertica l stabilize rwe b fo rcracks . Pag e 2 8 3 0 Ap r200 8 

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11 . 12 . 13 . 14 . 15 . 

### 16 . 17 , 

### 18 , 19 . 20 , Remov e th e rudder .

- Visuall yexamin e th e hing e pi n fo rcracks , corrosio n an d fi t i n th e composite .

- O n aircraf t tha t hav e a sleev e installe d ove rth e hing e pin , replac e th e sleev e i f i t i s damage d o rworn .

- Lubricat e th e hing e bushes . (Refe rt o Chapte r55-40) . D o a visua l inspectio n an d a ta p tes t o f th e rudder .

- Examin e th e ski n fo rdelamination , cracks , dent s an d scratches .

- Examin e th e pain t fo rchips , scratche s an d U V damage .

- Examin e fo rdamag e t o th e core .

- Examin e fo ra disbon d betwee n th e ski n an d th e core . Visuall yexamin e th e drai n hole s i n th e rudder . Mak e sur e tha t the yar e open . Viewthroug h th e acces s hole s i n th e vertica l stabilize rspa ran d visuall yinspec t interna l composit e component s fo rdisbondin g wit h skin , an d fo rdelaminatio n an d cracks . Examin e th e rudde rmountin g an d contro l cabl e connections . Examin e th e rudde rsuppor t bracket . Visuall yexamin e th e rudde rpivo t bearin g fo r corrosio n an d wear . Examin e th e botto m edg e o f th e rudder . Loo k especiall yfo rcrack s an d deformation . Examin e th e rudder-sto p reinforcemen t bars . Loo k especiall yfo rcrack s an d corrosion . Examin e th e tri m actuator . Loo k especiall y fo rcorrec t attachmen t an d wear . Examin e th e for k

assembl yo n th e tri m actuator . Loo k

especiall yfo rcrack s an d corrosion . Remov e th e horizonta l stabilizer . Examin e th e horizonta l stabilize rfo rdamage . (Refe rt o Chapte r55-10) . Doc#DA201-C 1 Rev . 1 3 20 0 

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22 . 23 . 24 .

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### 29 , Interva l (Fligh t Hours )

Inspectio n Item s Visuall yexamin e th e bushing s at th e aft horizonta l stabilize rattachment . Examin e fo rcorrosion , cracks , delaminatio n o rcrack s i n composit e aroun d bushing . Remov e th e elevato rfro m th e horizonta l stabilize r(Refe rt o Chapte r55-20) . Examin e th e elevato rfo rdamage . Loo k especiall yfo rcorrec t attachmen t an d loc k devices . (Refe rt o Chapte r27-30) . D o a visua l inspectio n an d a ta p tes t of th e elevator .

- Examin e th e ski n fo rdelamination , cracks , dent s an d scratches .

- Examin e th e pain t fo rchips , scratche s an d U V damage .

- Examin e fo rdamag e t o th e core .

- Examin e fo ra disbon d betwee n th e ski n an d th e core . Visuall yexamin e th e drai n hole s i n th e elevator . Mak e sur e tha t the yar e open . D o a visua l inspectio n o f th e elevato rhinges . Loo k especiall yfo rcracks , corrosio n an d th e fi t of th e clevi s pi n i n th e hinge . Remov e an d replac e th e elevato rhing e hardware . Examin e th e elevato rhinge s an d contro l horn . Chec k

th e laminat e aroun d th e hinge s an d th e contro l hor n fastener s fo rcracks , corrosio n o rdelamination . Loo k especiall yfo rto o muc h play . Playallowed :

- Axial : ±1,0 0 m m ( ±0.0 4 in) .

- Radial : ±0,2 5 m m ( ±0.01 in) . Visuall yexamin e th e bronz e bushing s i n th e elevator . Examin e fo rcorrosion , cracks , an d correc t tolerance . 

### 5 0 J 10 0

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30 .

31 . 32 . 33 . 34 . 35 . 

## Tim e Limit s an d Maintenanc e Checks Interva l (Fligh t Hours ) Inspectio n Item s (5 0 j _100 ^ Remov e th e elevato rhorizonta l push-ro d an d examin e i t fo rdamage . Loo k especiall y fo rru b mark s an d excessiv e wear . Th e maximu m wea rpermitte d i s 0.38 1 m m (0.01 5 in) . Measur e th e amoun t o f wea ra s follows :

- Tak e a measuremen t o f th e push-ro d diamete ra t th e edg e o f th e pain t

- Tak e a measuremen t o f th e push-ro d diamete ra t th e middl e o f th e wea rmar k

- Compar e th e tw o measurements . I f th e maximu m wea rpermitte d i s exceeded , replac e th e push-rod . Instal l th e pushrod . (Refe rt o Chapte r27-30) . Instal l th e elevato rbac k o n th e horizonta l stabilize r(Refe rt o Chapte r55-20) . Examin e th e forwar d mountin g bracket s fo r th e horizonta l stabilizer . Replac e al l o f th e mountin g hardware . (Refe rt o Chapte r12-20) . O n th e horizonta l stabilizer : Replac e th e fou rbolt s whic h attac h th e horizonta l stabilize rmoun t plat e t o th e vertica l stabilizer . Instal l th e horizonta l stabilizer . (Refert o Chapte r55-10) . Instal l th e rudder , (Refe rt o Chapte r55-40) . 20 0

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## Tim e Limit s an d Maintenanc e Checks 

# Diamond . DA20-C 1 AM M G . Wing s Al l item s performed , th e findings , a s wel l a s thei rcorrectio n mus t b e recorde d i n accordanc e wit h a n approve d procedure s manual . Contac t Diamon d Aircraf t i f damage s ar e determine d whic h canno t b e repaire d i n accordanc e wit h a n approve d procedure s manual .

Inspectio n Item s Interva l (Fligh t Hours )



# r 5 0 

## > -foT" * 20

0 100 0 600 0 Initials .

3 . Examin e th e complet e surfac e of th e wings . Loo k especiall yfo rdamag e (dents , cracks , hole s an d delamination) . Examin e th e pain t coat . D o a visua l inspectio n an d a ta p tes t o f th e uppe ran d lowe rwin g skins . Examin e fo r damag e t o th e cor e o ra disbon d betwee n th e ski n an d core . D o a visua l inspectio n an d a ta p tes t o f th e leadin g edge . Examin e fo rdisbond s an d crack s abov e o rbelo wth e overla p seam . D o a visua l inspectio n an d a ta p tes t t o examin e th e mai n spa rbondin g wit h th e win g skins . Remov e th e wing s (Refe rt o Chapte r57-10) .

- Examin e th e Abolt s an d bushing s fo r securit yi n surroundin g composite , tightnes s o f fi t o f pin/bolt , cracks , corrosion , wea ran d distortion .

- Replac e th e Abolt s i f ther e i s mor e tha n 0. 1 m m (0.00 4 in ) o f radia l play .

- Greas e th e Abolts .

- Examin e th e B-bolt s an d bushing s fo r securit yi n surroundin g composite , tightnes s o f fi t o f pin/bolt , cracks , corrosion , wea ran d distortion .

- Replac e th e B bolt s i f ther e i s mor e tha n 0, 1 m m (0,00 4 in ) o f radia l play ,

- Greas e th e B-bolts . (Refe rt o Chapte r12-20) . D o a visua l inspectio n an d a ta p tes t o f th e win g root s (i n fron t an d behin d th e spar ) t o examin e th e bondin g wit h th e skins . Pag e 3 2 3 0 Ap r200 8 

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# Diamond . Tim e Limit s an d Maintenanc e Checks Inspectio nItem s Initials .

10 . 11 .
12 . 13 .
14 . At th e lowe rwing , remov e th e tie-dow n rin g t o chec k fo rdamag e t o th e hole . Chec k fo r delamination , crack s an d elongatio n o f th e hole . Visuall yexamin e th e interna l rib s throug h th e lowe rwin g inspectio n panels .

- Chec k fo rth e conditio n o f th e laminat e o n th e ribs .
- Chec k fo rcrack s an d delaminatio n aroun d th e bellcran k

bracket s an d a disbon d betwee n th e bracke t an d rib .

- Chec k th e conditio n o f th e bellcran k brackets . Loo k

especiall yfo rcracks , elongatio n o f th e bellcran k mountin g holes , corrosio n an d chippe d paint . D o a visua l inspectio n an d a ta p tes t o f th e trailin g edg e spar .

- Examin e fo rth e conditio n o f th e laminat e an d bon d o f th e trailin g edg e t o th e skin .

- Examin e fo rth e bondin g o f th e fla p an d ailero n hinge s t o th e trailin g edg e an d skin .

- Examin e th e bondin g o f th e fla p up-sto p ri b t o th e trailin g edg e an d skin . Visuall yexamin e th e mai n spa rflang e join t an d web , outboar d fro m th e roo t rib . Loo k throug h th e roo t ri b openings . Loo k fo rsign s o f damag e (delamination) . Visuall yexamin e th e mai n spa rwe b sandwic h structure , outboar d fro m th e roo t rib . Loo k

throug h th e roo t ri b openings . Loo k fo rconditio n o f laminate , delamination , conditio n o f core . Visuall yexamin e th e win g root s (i n fron t an d behin d th e spar ) t o inspec t th e joint s wit h th e mai n spa ran d spa rstump . Examin e th e conditio n o f th e laminate . Loo k especiall y fo rdamag e (crack s an d delamination) . Visuall yexamin e th e mai n bol t bushin g i n th e spa rweb . Loo k

especiall yfo rcorrosio n o rwea ro f bushing , bon d o f bushin g i n spa r stump . Mak e sur e o f a tigh t fi t of th e mai n pi n withi n th e bushing . Remov e th e aileron s fro m th e wings . (Refe rt o Chapte r57-60) , Doc#DA201-C 1 Rev . 1 3 

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# Diamond . DA20-C 1 AM M

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17 . 18 .



### 19 . 20 . 

### 21 . 22 . 23 , Inspectio n Item s Visuall yexamin e th e ailerons . Loo k especiall yfo rdamag e (dents , cracks , hole s an d delamination) . D o a visua l inspectio n an d ta p tes t o f th e ailerons .

- Examin e th e pain t fo rchips , scratche s an d U V damage .

- Inspec t th e ski n fo rdelamination .

- Inspec t fo rdamag e t o th e cor e o r disbon d betwee n th e ski n an d th e core .

- Inspec t th e rib s fo rbondin g wit h th e skins . Remov e an d replac e th e ailero n hing e hardware . Examin e th e ailero n hinge s an d contro l horns . Chec k

th e laminat e aroun d th e hinge s an d th e contro l hor n fastener s fo r cracks , corrosio n o rdelamination . Loo k especiall yfo rto o muc h play . Playallowed :

- axial ; ±1.0 0 m m ( ±0.0 4 in) .

- radial : ±0.2 5 m m ( ±0.0 1 in) . Visuall yexamin e th e drai n hole s i n th e ailerons . Mak e sur e tha t the yar e open . Instal l th e aileron s bac k o n th e wings. ' (Refe rt o Chapte r57-60) . Visuall yexamin e th e mas s balanc e attachmen t throug h th e acces s hol e o n th e lowe rsurface . Inspec t fo rcrack s i n th e laminat e an d bondin g past e aroun d th e fasteners . Remov e th e flap s fro m th e wings . (Refe rt o Chapte r57-50) . Examin e th e flaps . Loo k especiall yfo r damag e (dents , cracks , hole s an d delamination) . Interva l (Fligh t Hours )

Pag e 3 4 3 0 Ap r200 8 

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## y" 

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### Initials . 24 .

25 .

26 . 27 .

28 , D o a visua l inspectio n an d ta p tes t of th e flaps .

- Examin e th e pain t fo rchips , scratche s an d U V damage .

- Inspec t th e ski n fo rdelamination .

- Inspec t fo rdamag e t o th e cor e o r disbon d betwee n th e ski n an d th e core .

- Inspec t th e rib s fo rbondin g wit h th e skins . Remov e th e fla p push-rod s an d examin e them fo rdamage . Loo k especiall yfo rru b mark s an d excessiv e wear . Th e maximu m wea rpermitte d i s 0.12 7 m m (0.00 5 in) . Measur e th e amoun t o f wea ra s follows :

- Tak e a measuremen t o f th e push-ro d diamete ra t th e edg e o f th e pain t

- Tak e a measuremen t o f th e push-ro d diamete ra t th e middl e o f th e wea rmar k

- Compar e th e tw o measurements . I f th e maximu m wea rpermitte d i s exceeded , replac e th e push-rod . Instal l th e pushrods . Remov e an d replac e th e fla p hing e hardware . Examin e th e fla p hinge s an d contro l horn . Chec k th e laminat e aroun d th e hinge s an d th e contro l hor n fastener s fo rcrack s o r delamination . Loo k especiall yfo rto o muc h play . Playallowed :

- Axial : + 1,0 0 m m ( + 0,0 4 in )

- Radial : ±0,2 5 m m ( ±0,01 in) . Instal l th e flap s bac k

o n th e wings , (Refe rt o Chapte r57-50) . 

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Maintenanc e Check s 

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### 100 0 600 0 Initials . 29 .

30 . 

### 31 . 32 . 33 .

34 . Remov e th e fla p an d ailero n bellcran k acces s panel s i n th e win g (Refe rt o Chapte r 52-40) .

- Examin e th e ailero n an d fla p contro l system . Loo k

especiall yfo rcorrec t attachmen t an d loc k

device s (Refe rt o Chapte r27-1 0 an d 27-50) .

- Instal l th e acces s panels . Examin e th e pito t head . Loo k especiall yfo r correct attachment . Examin e th e ven t an d drai n hole s i n th e wings , fuselag e an d contro l surfaces . Mak e sur e tha t the yar e clear . D o a tes t fo raxia l pla yi n th e B-bolts . (Refe rt o Chapte r57-10) . D o a visua l inspectio n an d a ta p tes t o f th e spa rbridge .

- Examin e th e conditio n o f th e laminate s an d th e bon d t o th e fuselage . Loo k especiall yaround :

- Th e L H an d R H A-bol t bushing .

- Th e B-bol t bushing .

- Th e ML G brackets .

- Th e L H an d R H to p af t oute rcorner s (behin d th e back-rest) . D o a visua l inspectio n o f th e insid e spa r bridge . D o a visua l inspectio n an d a ta p test . Chec k fo rdelaminatio n o f fuselag e ski n outboar d o f th e sea t fastene rthroug h th e sid e o f spa rbridge .

Pag e 3 5 3 0 Oc t 200 8 

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Inspectio n Item s Interva l (Fligh t Hour s 20 0 

### 100 0 600 0 Initials . 35 .

36 . 37 . 38 . Remov e th e ailero n push-rod s an d examin e the m fo rdamage . Loo k especiall yfo rru b mark s an d excessiv e wear . Th e maximu m wea rpermitte d i s 0.25 4 m m (0.01 0 in) . Measur e th e amoun t o f wea ra s follows :

- Tak e a measuremen t o f th e push-ro d diamete ra t th e edg e o f th e pain t

- Tak e a measuremen t of th e push-ro d diamete ra t th e middl e o f th e wea rmar k

- Compar e th e tw o measurements . I f th e maximu m wea rpermitte d i s exceeded , replac e th e push-rod . Instal l th e ailero n push-rods . (Refe rt o Chapte r27-10) . Visuall yexamin e th e mai n pi n bushin g i n th e spa rstump . Replac e th e mai n pi n bushin g i f i t i s damaged . Visuall yexamin e th e mai n pi n bushin g i n th e spa rbridge . Replac e th e mai n pi n bushin g i f i t i s damaged . Instal l th e wings . (Refe rt o Chapte r57-10) .

Doc#DA201-C 1 Rev . 1 4 

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## Tim e Limit s an d Maintenanc e Check s 

# Diamond . DA20-C 1 AM M H . Genera l Al l item s performed , th e findings , a s wel l a s thei rcorrectio n mus t b e recorde d i n accordanc e wit h a n approve d procedure s manual . Contac t Diamon d Aircraf t i f damage s ar e determine d whic h canno t b e repaire d i n accordanc e wit h a n approve d procedure s manual .

Inspectio n Item s Interva l (Fligh t Hours ) 

### 100 ^ 20 0 

### 100 0 600 0 Initials .

2 . Examin e th e pitot-stati csystem . Loo k especiall yfo rleaks .

- D o a low-rang e stati clea k tes t (Refe rt o Chapte r34-10) .

- D o a pito t tes t (Refe rt o Chapte r34-10) .

- Mak e sur e th e pitot-stati csyste m i s clean . Perfor m a functiona l chec k o f th e pito t stati c hea t syste m (i f installed) . Inspectio n Interval ; 100 0 hrs . o r1 2 months , whicheve r come s first . Refe rt o chapte r34-1 0 Lubricat e th e airplane .

- Refe rt o chapte r12-2 0 Measur e th e pla yi n th e ailero n an d elevato r control s wit h th e contro l surface s locke d (Refe rt o Chapte r27-30) . Loo k especiall y fo rto o muc h play . D o th e tes t at th e to p of th e contro l stick . Maximu m pla yallowed :

- 1 0 m m (0.37 5 in )

- Refe rt o Chapte r27-10 . D o a functio n tes t o f th e ailero n contro l system .

- Refe rt o Chapte r27-10 , D o a functio n tes t o f th e rudde rcontro l system .

- Refe rt o Chapte r27-20 , D o a functio n tes t o f th e elevato rcontro l system .

- Refe rt o Chapte r27-30 . Pag e 3 8 3 0 Oc t 200 8 

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Inspectio n Item s Interva l (Fligh t Hours )



# do j ^P5 ' ^ 20 0 100 0 600 0 initials . 

## 7 ^ 8 .

10 . 11 . D o a n actuator-moto rtes t o f th e trim-system . Loo k especiall yfo rcorrec t operatio n an d indication .

- Refe rt o Chapte r27-31 . D o a functio n tes t o f th e fla p syste m (Refe r t o Chapte r27-50) . Loo k especiall ya t th e pre-load . Wit h th e flap s se t t o CRUIS E i n th e u p position .

- Correc t pre-load : 3 0 - 5 0 N (6.7-11. 2 lbs ) D o a n operationa l tes t o f th e externa l lights . Examin e th e airplane . Loo k especiall yfo r loos e item s an d tools . Clos e al l acces s panels . Instal l thes e items :

- Engin e cowlings .

- Th e instrumen t pane l cover .

- Th e sea t shells .

- Th e control-stic k

boots . 

# < l

WARNING : D O NO TLE TPERSON S INT O TH E DANGE R ARE AO F TH E

PROPELLER . PROPELLER S CA N CAUS E INJUR YO R DEATH . WARNING : SE TTH E PARKIN G BRAK E T O ON . I F YO U D O NO TD O THI S TH E

AIRPLAN E CA N MOVE . THI S CA N CAUS E INJUR YO R DEATH .



# S f 12 . 13 . 14 .

15 , 16 . 17 . Se t th e parkin g brak e t o ON . Pu t th e chock s agains t th e mai n airplan e wheels . D o th e pos t maintenanc e operationa l test .

- Fo rth e engin e ru n procedure s refe rt o th e DA20-C 1 Fligh t Manual ,

- Fo rth e operationa l tes t refe rt o TC M Maintenanc e Manua l Chapte r23 ,

- Recor d th e dat a (Refe rt o Paragrap h 7) . Examin e th e engin e fo rleakage . Mak e sur e th e engin e oi l filte ri s tight ,

- Refe rt o Chapte r79-00 , D o a tes t flight . Recor d th e engin e groun d tes t an d th e fligh t tes t report s i n th e Airplan e Maintenanc e Log . 

# o

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## Tim e Limit s an d Maintenanc e Check s 

# Diamond . DA20-C 1 AM M

5 . Maintenanc e Repor t Complete a cop

yof th e Maintenanc e Repor t afte ral l o

f th e applicabl e maintenance task s i n th e Maintenance Checklis t have bee n initialed . DA20-C 1 Airplan e Seria l Number : Check : 

### REMARKS : 

# 1 /6DA£ _ 

# noy^ i (5 0 hr . Registratio n Number : 

## .^ooV . A. / :^^C, ^ 20 0 hr. , 100 0 hr. , 600 0 hr. . Annual ) |



### Th e airplan e i s airworth ywit h respec t t o its maintenance condition . Place : Date : Authorized : 

# 1 7 Pag e 4 0 3 0 Oct 2008 

# 05-20-0 0 Doc#DA201-C 1 Rev . 1 4

# EXHIBI T 2•••• ^ ^•• ^

DAT E F t DAIL V TOTA L HRS . MIN . OTA L AI R TIM E SINC E MFG . HRS . MIN . NOTE : ENGINEERIN G RCCOR D US E BOT H PAOE l AN D AIMAN YLINK ! A l REQUIRE D rO R COMPLE T

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## N383C A Airfram e lo g for 100 inspection s Date : 4/19/200 9 Tac htime : 932. 1 Airframe total time : 932. 1 Engin e total lim e sinc e new : 932. 1 Propelle r total tim e sinc e new : 249. 9 Lubricate dAircraf

t serx'ice dtire s an dbattery chec k op s o f ELT i s o k check . ELT battery du e date SEP T /201 0 all A.D' s checke dthroug h2009-7 . 1 certif y tha t thi s aircraf

t wa s inspecte dl.A.W . FA R43APP/D 100 HOURINSPETIO Nan ddetermen t i t t o b e in air^^'orlh y conditio nEND . PAU LMASARACpilArA& P10456937 4

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## AIRFRAM Elo g 5 0 inspectio n Engin e tim e sinc e new : 982. 2 N383C A DATE : 05/31/200 9 Tac htime : 982. 2 Aircraf t total time : 982. 2 Lube daircraft , checke dtire s andbrake fluid . serA'icedbattery JA W5 0 HOUR N^IMI^SIM'^PT? ! 

## ^iV'p?.'^'5^?]^B^inirwonh;ct^tio ne"^^ ^ NAM ESAME RELSAYE D .:^^--:Crr:::-: . A& P324567 5 V ^ 

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N383C A DATE : 05/31/200 9 Tac htime : 982. 2 .Aircraf t tota l time : 1396. 8 Inspecte dNLGan dfoun ddamage do nassy . Remove dan dreplace dassy . Wit hnew VF H 20-3220-08-0 0 S/

NCS0700186-10000 . Remove dan dreplace dwit hne w th e shoc k absorber s P/

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M AN D I S DETERMEN D T O B Ei nairworth y conditio nend^^ ^ ^ NAM EP.AU

LMASARACCHI A Qj)/^;^^^,J^...- ^ .A& P10456937 4

CARRfE D FORWAR D

## CERTIFICAT EO FSERVICE I hereby certif

y tha t I hav e thi s dat

e servedby regula

r U.S . mail , postag e prepaid , a norigina l an d one (1 ) copy o f

th e foregoing Motionfo

r Partia l Summar y Judgmen

t addresse dto : Attention : Hearing Docke

t Clerk , AGC-43 0 Wilbu r Wrigh t Building Federa l Aviatio nAdministratio n 800 Independenc e Avenue , S.W . Room201 4 Washington , D.C . 2059 1 I hereby certif

y tha t I hav e thi s dat

e sen t vi afacsimile andfirs t

clas s mai l acopy o f

the foregoing Motionfo r Partia l Summar y Judgmen

t addressedto : Th e Honorabl e Ronni e A . Yode r Chief Administrativ e La

w Judg e Offic e o f Hearings , M-20 U . S . Departmen

t o f Transportatio n 120 0 Ne w Jersey Ave. , S.E . Eas t Buildin g GroundFloor , Roo mE12-320 Washington , D C 2059 0 Tel : 20 2 366-321 2 Fax : 20 2 366-753 6 Zachar y M . Berman , Esq . FA A Easter nRegion , AEA- 7 1 Aviatio nPlaza , Room56 1 Jamaica , NY 1143 4 Tel : 71 8 553-325 8 Fax:71 8 533-569 9 Date dthi s 31t hda y o f Ma y 2011 . Respectfull y s; GREBQRY/S^VINTON , ESQ . Th e Ayiaticoj^aw Fir

m On e ResearchCourt , Suit

e 45 0 Rockville,M D 2085 0 Counsel fo r

Responden

t