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SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM

MODEL 200

SERIES PISTONSINGLE ENGINE AIRCRAFT

PROGRAMA

DE AERONAVEGABILIDAD CONTINUADA

CAP

TRAVEL AIR E.I.R.L.

CARATULA

AUTOR: MELQUIADES CHAVEZ GALDOS

FECHA: 08-ABRIL-2010 REVISIN: ORIGINAL PAGINA: 1

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PROGRAMADE AERONAVEGABILIDAD CONTINUADA

CAP

MANUAL N

REVISION N

ASIGNADO A:

FECHA: 08-ABRIL-2010 REVISIN: ORIGINAL PAGINA: 2

ORIGINAL

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INDICE GENERAL

LISTA DE CONTENIDO PAGINA

CARTULA DEL MANUAL 1

CARATULA DE ASIGNACION DEL MANUAL 2

INDICE GENERAL 3 al 5

APLICABILIDAD 6

LISTA DE PAGINAS EFECTIVAS 7 al 9

Pgina en blanco 10

A.0.- PROGRAMA DE AERONAVEGABILIDAD CONTINUADA (CAP) 11

A.1 INTRODUCCIN 11

A.2 POLITICA 11

A.3 OBJETIVO 11

A.4 ORGANIGRAMA 12

Pgina en blanco 13

B.0.- CONTROL DEL PROGRAMA DE AERONAVEGABILIDAD CONTINUADA (CAP) 14

B.1 CARATULA DEL PROGRAMA 14

B.2 CARATULA DE ASIGNACION DEL PROGRAMA 14

B.3 NUMERO DE CONTROL Y LISTA DE DISTRIBUCION DEL PROGRAMA 14

B.4 APROBACION Y REVISIN 15

B.5 REGISTRO DE REVISIONES 16

Pgina en blanco 17

INTRODUCCION AL PROGRAMA DE AERONAVEGABILIDAD CONTINUADA 18

1.0 DISCUSION 18

1.1 INTRODUCCION AL CAP 18

1.2 OBJETIVO DEL CAP 18

2.0 (DETALLES IMPORTANTES DEL SISTEMA / ESTRUCTURAL) SSDS 19

2.1 FUNDAMENTOS USADOS PARA SELECCIONAR LOS SSDs 19

2.2 LOS SSDs FUERON SELECCIONADOS BASADOS EN LO SIGUIENTE 19

A. EXPERIENCIA EN EL SERVICIO 19

INDICE GENERAL (Cont....)

FECHA: 08-ABRIL-2010 REVISIN: ORIGINAL PAGINA : 3

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B. BOLETINES DE SERVICIO, NEWSLETTERS Y SERVICEKITS 19

C. ANALISIS 19

D. PRUEBAS 20

C. INSPECCION DEL AVION 20

3.0 REPORTE Y COMUNICACIONES 20

3.1 REPORTANDO LAS DISCREPANCIAS 21

3.2 DISPOSICION DEL FORMATO DE DISCREPANCIAS 21

3.3 ACCIONES DE SEGUIMIENTO DEL FABRICANTE 21

4.0 INFORMACION BASICA 22

4.1 INSPECCION 22

1. GENERAL 22

2. MATERIALS AND EQUIPMENT 22

3. PROCEDURES 23

A. Surface Cleaning 23

B. Applicantion of Penetrant 23

C. Removal of Excess Penetrant 23

D. Application of Developer 23

E. Interpretation of Indication 24

4.2 MANUALS 24

4.3 SERVICE LETTERS/BULLETINS 24

5.0 APPLICABILITY/LIMITATIONS 24

6.0 SIGNIFICANT DETAILS 25

6.1 CAP FORMS 25

6.2 REPAIR INFORMATION/MODIFICATION 25

DISCREPANCE REPORT 26

SECTION I TECHNICAL DOCUMENT REFERENCE 27

SERVICE MANUALS 27

SERVICE BULLETIN 27

Pgina en blanco 28

SECTION II - LISTING OF CONTINUED AIRWORTHINESS PROGRAM INSPECTIONS 29

INDICE GENERAL (Cont....)



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SECTION III CONTINUING AIRWORTHINESS PROGRAM INSPECTION 30

27-30-02 Elevator Trailing Edge andTrim Tab Inspections 30-31

28-30-01 Quick Drain Valves Fuel Reservoir and Fuel Tanks 32-3328-40-01 Fuel Gaging Systems 34

29-10-01 Hydraulic Hose Replacement and Hydraulic Component Replacement 35-36

32-50-02 Nose Gear Steering Collar and Upper Torque Link 37-39

39-00-01 Engine Compartment Wiring and Equipment Installation 40

53-40-01 Fuselage Wing Strut Attach Forging 41-42

53-40-02 Fuselage Wing Attachments 43-44

53-40-04 Fuselage Vertical Fin Attachments 45-49

53-40-06 Main Landing Gear Support Fittings 50-51

55-10-01 Horizontal Stabilizer Aft Attach Bracket 52-53

55-30-01 Vertical Tail Fin Fuselage Attachments 54-59

57-10-03 Front Spar Splice LH Aft 60-61

57-10-04 Front Spar Splice LH Aft 62-63

57-10-06 Wing Fuselage Attach Fittings 64-65

57-10-11 Wing Strut Tube 66

Pgina en blanco 67


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APLICABILIDAD

MODEL YEAR SERIAL

207/T207 1969 THRU 1984 20700001 THRU 20700788

OB-1001 AO DE FABRICACION 1969 SERIAL NUMBER 20700055

OB-1888 AO DE FABRICACION 1974 SERIAL NUMBER 20700266


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LISTA DE PGINAS EFECTIVAS

PAGINA REVISION FECHA

1 ORIGINAL 08-ABR-2010













14 ORIGINAL 08-ABR-201015 ORIGINAL 08-ABR-2010














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LISTA DE PGINAS EFECTIVAS (Cont)































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LISTA DE PGINAS EFECTIVAS (Cont)














FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 9

D i r e c c i n G e n e r a l d e A e r o n u t i c a C i v i l

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PAGINA INTENCIONALMENTE

DEJADO EN BLANCO


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A.0 PROGRAMA DE AERONAVEGABILIDAD CONTINUADA (CAP)

A.1 INTRODUCCIN

El presente Programa de Aeronavegabilidad Continuada ha sido desarrollado porTRAVEL AIR E.I.R.L. en base al Manual D5121-1-13 publicado por Cessna AircraftCompany, como un complemento al Programa de Mantenimiento Aprobado por laDGAC.

Este Manual ser usado por TRAVEL AIR como parte de su Programa deMantenimiento, para garantizar la Aeronavegabilidad continuada de sus Aeronaves. losICA (Inspecciones de aeronavegabilidad Continuada) son fichas de inspeccin dondese muestran los cumplimientos INICIAL y REPETITIVO .

A.2 POLITICA

TRAVEL AIR E.I.R.L., posee un equipo de trabajo de alto nivel profesional cuyasacciones diarias de mantenimiento las ejecutamos con un elevado profesionalismopara garantizar la aeronavegabilidad continua de nuestras aeronaves, nuestra visin deempresa est basada en los siguientes principios:

INTEGRIDAD PERSONAL como expresin de disciplina, orden, respeto,honestidad y entusiasmo.

CREATIVIDAD E INNOVACIN como parte de nuestro reto diario para elmejoramiento contino.

PRODUCTIVIDAD en nuestro trabajo y en el empleo de los recursos materiales.

CONSCIENCIA en la ejecucin de tareas de mantenimiento libre de errores y el

COMPROMISO leal con la compaa y con las realizaciones de calidad.

SEGURIDAD EN LAS OPERACIONES: Actitud proactiva y acciones dinmicaspreservando la seguridad e integridad de las aeronaves.

A.3 OBJETIVO.

El objetivo de este Programa de Aeronavegabilidad Continuada es garantizar laaeronavegabilidad de cada una de nuestras aeronaves para brindan un servicioms eficiente con un alto grado de seguridad para nuestros clientes.


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A.4 ORGANIGRAMA

Este organigrama obedece nicamente a los responsables directos de velar elcumplimiento del Programa de Aeronavegabilidad Continua (CAP).


GERENTE DE MANTENIMIENTO

JEFE DE CONTROL DE

CALIDAD

INSPECTOR DE

MANTENIMIENTO

ICA

CONTROL DE

MANTENIMIENTO

INSPECTOR DE

MANTENIMIENTO

NAZCA

SUPERVISOR DE

MANTENIMIENTO

ICA

SUPERVISOR DE

MANTENIMIENTO

NAZCA

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DEJADO EN BLANCO


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B.0 CONTROL DEL PROGRAMA DE AERONAVEGABILIDAD CONTINUADA (CAP)

B.1 CARATULA DEL PROGRAMA

Es la primera pgina de este Programa con el propsito de facilitar su identificacin.

B.2 CARATULA DE ASIGNACION DEL PROGRAMA

Es la Segunda Pagina de este Programa donde se registra el Numero del Manualasignado, el Nmero de Revisin actual y el nombre del departamento, entidad o aquien es asignado el presente el manual.

B.3 NUMERO DE CONTROL Y LISTA DE DISTRIBUCION DEL PROGRAMA

Los Programa asignados sern numerados correlativamente con un nmero decontrol. El departamento de Control de Mantenimiento mantendr una Lista deAsignacin de los Manuales en la que incluir el nmero de control y las revisiones quese han incorporado.

01 Direccin General de Aeronutica Civil (D.G.A.C.) (CD)

02 Gerencia de Mantenimiento

03 Departamento de Control de Calidad

04 Control de Mantenimiento

05 Estacin de Lnea Nazca

06 Departamento de Instruccin y Publicaciones

B.4 APROBACION Y REVISIN


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En esta seccin se establecen los procedimientos para que el CAP (Programa deAeronavegabilidad Continuada) se mantenga actualizado.

La revisin del CAP, es responsabilidad directa del Gerente de Mantenimiento, sin

embargo podr delegar esta funcin; toda vez que la DGAC emita una nueva Normatcnica, revisiones efectuadas por Cessna o cuando Travel Air considere convenientepara mejorar su Programa.

El responsable de efectuar la revisin recibir todas las sugerencias de revisiones almanual de los usuarios asignados, insertando las correcciones o modificaciones queconsidere necesarias; una vez realizada la revisin se insertara al el pie de pgina lafecha de la revisin seguido del N de revisin correspondiente, para posteriormentesolicitar a travs del Inspector Principal de Mantenimiento (IPM DGAC) su aceptacino aprobacin.

El responsable de la revisin remitir al IPM de Travel Air, a travs de mesa de partesdel MTC, una carta de presentacin con el logo tipo de la compaa y la firma delGerente de Mantenimiento junto con un ejemplar de las pginas revisadas y dos copiasde la lista de pginas efectivas.

Una vez aprobada o aceptada la revisin, con la refrenda del IPM en la lista de laspginas efectivas, el Departamento de Control de Mantenimiento sacar copiassuficientes de las revisiones para su distribucin a las diferentes reas.

Las revisiones sern distribuidas por el encargado del Departamento de Control deMantenimiento con un cargo de entrega, ser responsabilidad del usuario el insertar lasrevisiones de acuerdo con la lista de pginas efectivas.

B.5 REGISTRO DE REVISIONES


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REVISIONFECHA DEREVISION

FECHA DEAPROBACION

PREPARADO POR

ORIGINAL 08-05-2010 CARLOS PALACIN CORCUERA


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DEJADO EN BLANCO

INTRODUCCION AL PROGRAMA DE AERONAVEGABILIDAD CONTINUADA

1.0 DISCUSION.


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El programa de la aeronavegabilidad Continuada (CAP) consiste en recomendaciones deinspeccin, que cuando se combinan con los requisitos de mantenimiento existentes,ayudar a mantener la aeronavegabilidad continuada de la aeronave.

1.1 INTRODUCCION AL CAP.

Las aeronaves contenidas en este CAP, fueron entregados (cuando fueron vendidos) conlos programas de inspeccin recomendadas. Manuales de mantenimiento actualizadoscontinuamente, complementados con los boletines del servicio e informacin para elpropietario fueron proporcionados (mediante subscripciones con Cessna) con la intencinde mantener la aeronavegabilidad de las aeronaves.

Debido a que estas aeronaves han sido asignados a variadas misiones (vuelos privados,tursticos, paracaidismo etc.), el tipo de cuidado que se le presta, as como elenvejecimiento general e ndice de uso (horas de vuelo del avin) , Cessna consideranecesario proporcionar requerimientos adicionales a los programas de inspeccin como un

medio de garanta adicional para que los aviones puedan continuar siendo aeronavegables.De la experiencia que Cessna ha adquirido y el apoyo continuo de los reportes de campode las aeronaves, Cessna contina dando informacin de servicio para las aeronaves pormedio de los CAP.

Este CAP ha sido desarrollado por Cessna en conformidad con las directrices que figuranen el CAP GAMA Formato Spec # 7.

El CAP no intenta hacer cambios o sustituir, pero puede proporcionar informacin adicionalal MANUAL DE MANTENIMIENTO, boletines de servicio o cartas de servicio que sonaplicables.

1.2 OBJETIVO DEL CAP.Este CAP se ha desarrollado para asegurar la capacidad de la aeronave para performardentro de los parmetros de la certificacin original.

Los CAP estn direccionados hacia los componentes estructurales primarioy secundario, motor, Items elctricos y sistemas primario y secundariopara lograr este objetivo declarado de aeronavegabilidad continuada.

Condiciones para establecer las bases para que los Itemsdetallados en los CAP sean incluidos, la aeronave debe

reunir con las siguientes condiciones:A. La aeronave ha sido mantenida en concordancia con las recomendaciones de Cessna

o equivalente.

B. Cuando el CAP est dirigido a un componente o parte especfico, se da a entender quela inspeccin incluir la observacin y evaluacin de las areas alrededor de las partes yequipamientos. Cualquier discrepancia encontrada durante la inspeccin fuera delalcance del CAP deber ser comunicado a Cessna a travs del sistema de reporte decondicin existente de manera que se pueden realizar cambios al CAP en casonecesario.


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C. Los aviones modificados por un Certificado Tipo Suplementario (STC) no sonresponsabilidad de Cessna. Cualquier inspeccin requerida dentro de lo manuales de

Cessna o CAPs que tengan reas que hayan sido modificados por un STC sernautomticamente referidas al titular del STC, por el propietario y / u organizacin demantenimiento para la obtencin de las directrices de mantenimiento aprobadas por laFAA.

2.0 (DETALLES IMPORTANTES DEL SISTEMA / ESTRUCTURAL) SSD'S.

Los elementos designados para la inspeccin en este documento son esas estructuras osistemas que incluyen el motor y elctricos cuyos fallas podran causar la prdida o daossustanciales a la aeronave. Los trminos detalles estructuralmente importantes odetalles importantes del sistema (SSD) se aplicar a estos Items crticos. La seleccin yel seguimiento de estos SSDs es el ncleo del (CAP) Programa de Aeronavegabilidad

continuada.

2.1 FUNDAMENTOS USADOS PARA SELECCIONAR LOS SSD'S.

La flota Cessna series 200 fue diseada para vuelos comerciales y vuelos de placer. Sinembargo, desde su produccin en comn algunos de estos aviones tienen ms de 10.000horas de vuelo y otros son mayores de (20 aos) con pocas horas de vuelo, los mtodos yfundamentos utilizados para la seleccin de los SSD crticos se dispone en el prrafo 2-2,A. hasta la E.

2.2 LOS SSD'S FUERON SELECIONADOS BASADOS EN LO SIGUIENTE:

A. EXPERIENCIA EN EL SERVICIO.

La correspondencia del cliente y reportes de condicin tambin fueron revisadosdurante el proceso de seleccin de los SSDs crticos. Los informes (reportes) tambinfueron utilizados para seleccionar los items que eran similares en aplicacin para otrasaeronaves basadas en funcin a su diseo y carga.

B. BOLETINES DE SERVICIO, NEWSLETTERS, Y SERVICE KITS.

Los boletines de servicio han sido revisados y volvieron a tratarse los criterios deseguridad de vuelo para ayudar a seleccionar los SSD crticos. Algunos de estosdocumentos se consideran vitales para la operacin segura de la aeronave y en

consecuencia, la estructura afectada o componentes del sistema sern enumeradoscomo un SSD.

NOTA.Algunos de estos boletines pueden ya estar

incorporados dentro del programa demantenimiento del operador.

C. ANALISIS.

Se revisaron los anlisis existentes para identificar los componentes en

reas que puedan haber mostrado el potencial requerimiento deinspeccin adicional.


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D. PRUEBAS.

Se realizo una revisin de los resultados de las pruebas aplicables al diseo. Seevaluaron los resultados de las condiciones de carga junto con pruebas estticas y defatiga. Los datos resultantes se utilizaron para determinar si el componente debera serconsiderado como un SSD para su incorporacin dentro del CAP.

E. INSPECCION DEL AVION.

Aeronaves con muchos aos de operacin fueron desarmadas completamente para serinspeccionado con la finalidad de seleccionar los SSD. Inspecciones especiales

fueron realizadas a otras aeronaves con muchos aos de operacin paracomplementar estas inspecciones.

Los efectos de la corrosin no se han tenido en cuenta en la seleccin y justificacindel SSD o los efectos sobre la fatiga por estrs. Es difcil determinar los efectos de lacorrosin, pero como son recibidos los reportes de inspeccin del CAP, los tiemposde inspeccin sern ajustados como sea necesario dependiendo de la severidad de ladiscrepancia.

NOTA

Si una aeronave tiene un historial donde se hayan realizado vuelos dereconocimiento a baja altura sobre el terreno las inspecciones Inicial y Repetitivo

se reducen a la mitad.

3-0. REPORTE Y COMUNICACIONES.

Para que los CAP puedan tener xito en forma permanente, es esencial que exista un libreflujo de informacin entre el operador, la DGAC y Cessna. Los detalles significativos delos resultados de la inspeccin, reparaciones y modificaciones ejecutados deben sercomunicados a Cessna con el fin de evaluar la eficacia de sus procedimientos de controlrecomendadas y los intervalos de tiempo. En algunos casos, es posible obtener

extensiones en las frecuencias de inspeccin si la informacin obtenida sugiere la aparicinde problemas de fatiga a un mayor nmero de horas de vuelo de lo inicialmente previsto.

Adems, Items no considerados anteriormente para su inclusin en el CAP pueden serdescubiertos por el operador a travs de las inspecciones y los reportes de inspeccin.Estos Items sern evaluados por Cessna y si es de aplicacin general a las configuracionesde la aeronave en cuestin, se aadir al CAP para el beneficio de todos.

Se ha establecido e incorporado en este documento un sistema de reporte consecuente con lossistemas empleados por el CESSNA PROPELLER PRODUCT SUPPORT ORGANIZATION yregistrada en este CAP. Las copias de los formularios pertinentes estn disponibles para usted en laEstacin de Servicio de Cessna o el Servicio de Ingeniera de campo de la Fbrica.


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3.1. REPORTANDO LAS DISCEPANCIAS.

El reporte de las discrepancias es esencial para proveer y ajustar los parmetros de inspecciny los intervalos de tiempo en mayor o menor intensidad, as como la incorporacin o eliminacin delos SSD. Basado en los datos reportados, puede ser posible perfeccionar los mtodos de inspeccin,reparaciones y modificaciones involucrados en los SSD.Todas las rajaduras y corrosiones de gravedad encontrados en materia de inspeccin de un SSDsern notificadas a la Cesnna. Los resultados de la inspeccin SSD se informara en un formulariocomo se muestra en la pgina siguiente:

3.2. DISPOSICION DEL FORMATO DE DISCREPANCIAS.

Enviar todos los datos disponibles incluyendo las reparaciones, fotos, etc. a la siguientedireccin:

Cessna Aircraft CompanyAttn: CAP Program

Technical Support ServicesDept. 751

P.O. Box 7706Wichita, Kansas 67277

Fax 1-316-942-9006

NOTA

Este sistema no reemplaza la condicin de comunicacin del sistema dereportes para aquellos Items no cubiertos por el CAP .

3.3. ACCIONES DE SEGUIMIENTO DEL FABRICANTE.

Todos los reportes SSD sern revisados para ver si algunas de las siguientes acciones deberanser tomadas:

1. Chequear sus efectos en la integridad estructural u operacional.

2. Chequear otras aeronaves con altas cantidad de horas a fin de considerar laemisin de un boletn de Servicio.

3. Ver si un reforzamiento es necesario.

4. Revisar el CAP si es necesario.


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4.0. INFORMACION BASICA.

Este CAP aplica a los aviones Series 200. Refirase a los manuales deServicio/Mantenimiento individuales de la serie 200 para los especficos programas deinspeccin de su aeronave.

NOTA.- Desde el prrafo 4.1 hasta la pgina final se mantendrn tal como fueronpublicados en Ingles.

4.1. INSPECTION.

1. GENERAL

A. A recommended method of inspection is given; however, if the operator can show

that an alternate method is equal to or better than the suggested method fordetecting damage, then it will be considered as a possible alternate inspectionmethod.

B. The following general eddy current inspection shall be used where called out as"INSPECTION PROCEDURES" within Section III.

C. Eddy current inspect using an eddy current test instrument capable of detecting thesimulated cracks in a bolt hole and surface reference standard equivalent to theHRS-10A and SRS-123A standard available from NDT Engineering, 7056 S. 220th,Kent, WA 98032.

D. The following general liquid penetrant inspection shall be used where called out as

"INSPECTION PROCEDURES" within Section III.

E. Penetrant inspection is used to detect small cracks or discontinuities open to thesurface which may not be evident by normal visual inspection. Penetrant inspectioncan be used on most airframe parts and assemblies accessible for its application.The inspection is performed by applying a liquid which penetrates into surfacedefects so that visual indications are obtained by color contrast or fluorescence ofthe penetrant under the display of black light. The penetrant method of inspectionrequires that the surface in the inspection area be thoroughly clean and free ofpaint.

2. MATERIALS AND EQUIPMENT

A. Due to the high sensitivity and the ability to detect fatigue cracks open to thesurface, portable fluorescent penetrant system is required as the inspection methodwhen specified for penetrant inspection of specific areas of the airframe structure.

B. The following penetrant materials are used to make a complete self-containedfluorescent penetrant kit. There are several manufacturers of fluorescent penetrantmaterials which are satisfactory, provide the materials are used as a family groupand meet the requirements of QPL-25135. A family is a series of items required toperform a specific method or process of penetrant inspection which is furnished byone manufacturer and meet the requirements of QPL-25135.


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Equipment Manufacturer

ZA 43 Fluorescent Penetrant Kit Magnaflux Corporationcontains the following: 7300 W. LawrenceAvenue Chicago, IL

60656ZL-22A PenetrantZP-9B Nonaqueous DeveloperZP4 Dry Power DeveloperSKC-7 CleanerZB-32A Portable Black Light

3. PROCEDURES

A.Surface Cleaning

(1) The area to be inspected must be free from any dirt, grease, oil, paint or anycontaminants which would mask or close a defect open to the surface. Thesurface should be dry before applying the penetrant.

CAUTION: DO NOT USE TRICHLORETHYLENE AS A CLEANING AGENT ONTITANIUM OR HIGH NICKEL ALLOY MATERIALS.

(2) The penetrant materials and the area to be tested shall have a temperature of60F to 130F

B. Application Of Penetrant.(1) Completely cover the area of inspection with penetrant by brushing. Allow

penetrant to remain on the area for a minimum of 30 minutes. After 35 minutes,reapply using a scrubbing action. This will help in the removal of the penetrantfrom the surface by loosening the previously applied partially dried penetrant.

C. Removal Of Excess Penetrant.

(1) Remove excess penetrant from surface by wiping with a clean dry lint-free cloth.Remove remaining penetrant with a clean lint-free cloth, dampened with penetrantcleaner. Do not flush surface with penetrant cleaner as this will flush penetrantfrom defects. Examine inspection area under the black light to ensure removal of

all surface penetrant.

D. Application Of Developer.

(1) The essential step in applying developer is to get the minimum thicknesspossible..The best results are obtained by a very thin coating. The Film ofdeveloper should be slightly translucent. When applying dry power developer,thoroughly dust area, then blow off excess power. When applying nonaqueouswet developer from a pressurized can, spray a thin coat on the surface and allowto dry in ambient air. The developer liquid shall be agitated frequently to preventsettling of the solid particles in the liquid vehicle. The full dwell time afterdeveloper has been applied should be no less than 5 minutes.


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E. Interpretation of Indications.

(1) An 8X magnifying glass should be used to examine area unless indications arevisible to the naked eye. Any surface break will be revealed by fluorescentindication on a blueish background. A fluorescent line will indicate a crack and willbe sharply defined at first and the amount of bleeding gives a clue to the depth ofthe crack. Inspectors should watch indications grow, since the first sharpindications tell much of the nature of the defect, and the amount of bleeding givesinformation as to the extent. A deep discontinuity indication will reappear anumber of times when wiped clean and developer reapplied.

4.2. MANUALS.

Cessna has a number of documents that are useful to maintaining continuedairworthiness of aircraft:

Cessna 200 Series Service ManualCessna 200 Series Parts CatalogsCessna Single Engine Service Bulletin SummariesCessna Newsletter Summaries

For information regarding these documents, contact:

Cessna Aircraft Company Supply DivisionAttn: SPA DepartmentP.O. Box 949Wichita, Kansas 67201Fax 1-316-68-84187

4.3. SERVICE LETTERS/BULLETINS.

As an aid to the operator, a listing of all the Service Letters/Bulletins pertaining tothese 200 Series Aircraft CAPS, are listed in Section 1, titled: TECHNICALDOCUMENT REFERENCE. For information concerning the technical data included inthese Service Letters/Bulletins that apply to your aircraft, you may contact Cessna'sPropeller Technical Information Services, Department 753. The telephone number forcustomer assistance is (316) 941-7550/Fax 1-316-942-9006. A Service Bulletin Listing

Program, that provides a list of all Cessna Service Bulletins and Service Newsletters,applicable to a particular airplane model and serial number is also available fromCessna. This service is obtained by calling (316) 941-6118/Fax 1-316-342-9006.

5.0. APPLICABILITY/LIMITATIONS.

The Cessna 200 series aircraft have had many modifications that were accomplishedunder STC's by other organizations without Cessna Engineering involvement.Because Cessna does not have knowledge of the airworthiness of STC's, this reportcannot apply to those areas affected by such STC's and the STC holder shouldprepare a CAP for each particular modification.


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6.0. SIGNIFICANT DETAILS.

This section contains the significant details selected by the rationale process describedin paragraph 2-2. These items are considered significant to maintain continuedairworthiness of all Cessna 200 series models. Service Bulletins considered mandatoryfor airworthiness will be listed in Section 1, TECHNICAL DOCUMENT REFERENCE.

A summary of the CAPs is shown in the section titled: LISTING OF CONTINUEDAIRWORTHINESS INSPECTIONS. This can be used as a checklist by the operators.

6.1. CAP FORMS.

Each CAP will be listed on a form and will contain the following:

1. Continued Airworthiness Inspection Number.2. Title.3. Effectivity.4. Inspection Compliance.5. Initial.6. Repeat.7. Purpose.8. Inspection Procedure.9. Access/Location.10. Detectable Crack Size.11. Inspection Procedure.12. Repair/Modification.13. Comments.

6.2. REPAIR INFORMATION/MODIFICATION

Repairs may be made in accordance with the applicable Cessna Service/MaintenanceManual or FAA AC43-13 acceptable methods of alteration and repair. Any repair notcovered by the recommendations in this CAP Program may be coordinated with CessnaTechnical Information Services at Telephone (316) 941-8500/Fax (316) 942-6000


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CESSNA AIRCRAFT COMPAINYMODEL 200 SERIES

CONTINUED AIRWORTHINESS PROGRAM

DISCREPANCY REPORT

CAP'S NO: _______________AIRPLANE LOCATION: _________________S/N OF

AIRPLANE:_________

INSPECTION CONDUCTED: Date ___________Airplane Total Hours ______________ Cycles N/A

Component Total Hours____________ Cycles N/A

SERVICE HISTORY:

____________________________________________________________________________________

________________________________________________________________________________________________________________________________________________________________________

INSPECTION METHOD/LIMITS:

____________________________________________________________________________________

____________________________________________________________________________________

____________________________________________________________________________________

ACCESS REQUIRED:

____________________________________________________________________________________

____________________________________________________________________________________

____________________________________________________________________________________

REPAIR DESCRIPTION:

____________________________________________________________________________________

____________________________________________________________________________________

____________________________________________________________________________________

COMMENTS:

________________________________________________________________________________________________________________________________________________________________________

____________________________________________________________________________________

Enclose all available data including photos, sketches, etc to:

Cessna Aircraft Company

Attn: CAP Program

Technical Support Servies

Dept. 751

P.O. Box 7706

Wichita, Kansas 67277

FAX 1-316-942-9006


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SECTION I - TECHNICAL DOCUMENT REFERENCE

SERVICE MANUALS

Model Number Title

207 & T207(1969 1984) D2060-1-13 207 & T207 Series

To obtain Service Manuals, write to:Cessna Aircraft Company Supply DivisionAtt: SPA Dept

P.O. Box 949Wichita, Kansas 67201Fax 1-316-688-4746

SERVICE BULLETINS

Number Title Date Cap Insp

SE65-83 Aileron Hinge Inspection 9-03-65 57-50-02SE71-4 Improved Nose Gear Steering Collar 2-12-71 32-50-02SE81-1 Gear Warning/Fuel Pump Switch Cable Improvement 1-19-81 32-60-01

SE84-8 Fuel Reservoir Tank Quick Drain Valve Installation 3-16-89 28-30-01SE84-17 Horizontal Stabilizer Aft Attach Bracket 9-28-84 55-10-01SEB85-5 Elevator Trim Tab Actuator Attach Bracket Inspection 3-22-85 27-30-01SEB85-7 Elevator and Trim Tab Inspection 4-05-85 27-30-02SEB85-9 Rear Wing Spar Doubler Inspection. 5-03-85 57-10-05SEB93-4 Upper Left Forward Doorpost Inspection and Modification 3-26-93 53-10-02SEB87-4 Aileron Hinge Attachment 6-12-87 57-50-01SNL85-54 Revised Overhaul/Replacement Requirements for 11-27-85 29-10-01

Hydraulic System Components on Single Engine,Skymaster, and Crusader Airplanes.

SNL86-49 Main Landing Gear Actuator Mounting Bolts 12-12-86 32-30-01

Service Bulletins listed above, write to:Cessna Aircraft Company Supply DivisionDept 753C.P.O. Box 7706Wichita, Kansas 67277Fax 1-316-942-9006


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PAGINA INTENCIONALMENTEDEJADO EN BLANCO


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SECTION II - LISTING OF 207 SERIES CONTINUED AIRWORTHINESS PROGRAMINSPECTIONS

OB-1001 AO DE FABRICACION 1969 SERIAL NUMBER 20700055OB-1888 AO DE FABRICACION 1974 SERIAL NUMBER 20700266

ContinuedAirworthiness

ProgramInspection

Inspection ComplianceNumber

Title

DateInitial

Effectivity INITIAL REPEAT

27-30-02Elevator Trailing Edge and

Trim Tab Inspections20700001 Thru 20700788

3,000Hrs

3,000Hrs

28-30-01Quick Drain Valves FuelReservoir and Fuel Tanks

20700001 Thru 207007881,000Hrs

or 2 Yrs

1,000 Hrsor 2 Yrs

28-40-01 Fuel Gauging Systems 20700001 Thru 20700788

1,000

Hrsor 3 Yrs

1,000 Hrsor 3 Yrs

29-10-01Hydraulic Hose Replacement

and Hydraulic ComponentReplacement

20700001 Thru 207007885 Yrs or

OnCondition

5 Yrs orOn

Condition

32-50-02Nose Gear Steering Collar

and Upper Torque Link20700001 Thru 20700788

3,000Hrs

3,000Hrs

39-00-01Engine Compartment Wiringand Equipment Installation

20700001 Thru 207007886,000Hrs

or 5 Yrs

2,000Hrs

or 2 Yrs

53-40-01Fuselage Wing Strut Attach

Forging20700001 Thru 20700788

12,000Hrs

1,000Hrs

53-40-02 Fuselage Wing Attachments 20700001 Thru 2070078812,000

Hrs2,000Hrs

53-40-04 Fuselage Vertical FinAttachments

20700001 Thru 20700216 12,000Hrs

2,000Hrs

53-40-06 Main Landing Gear Fittings 20700001 Thru 207007883,000Hrs

1,000Hrs

55-10-01Horizontal Stabilizer Aft Attach

Bracket20700001 Thru 20700788

1,000Hrs

200Hrs

55-30-01Vertical Tail Fin FuselageAttachments

20700001 Thru 2070002112,000

Hrs6,000Hrs

57-10-03

1. 1222105-37 Stiffener -Front Spar Splice LH - Aft2. 0721402-5 Stiffener - FrontSpar Splice LH - Aft.3. 1222105-3 Web - FrontSpar Splice LH - Aft

4. 1222105-5 Web - FrontSpar Splice LH - Fwd5. Strut Attach Hole

20700001 Thru 20700788 15,000Hrs

3,000Hrs

57-10-04

1. 1222005-7 Stiffener FrontSpar Splice LH Aft2. 0721402-5 Stiffener FrontSpar Splice LH Aft3. 1222005-3 Web - FrontSpar Splice LH - Aft4. 1222005-5 Web - FrontSpar Splice LH - Fwd5. Strut Attach Hole

20700001 Thru 2070078815,000

Hrs3,000 Hrs

57-10-06 Wing Fuselage Attach Fittings 20700001 Thru 2070078812,000

Hrs3,000 Hrs

57-10-11 Wing Strut Tube 20700001 Thru 207007881,000Hrs

1,000 Hrs


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SECTION III - CONTINUING AIRWORTHINESS PROGRAM INSPECTIONAircraft CESSNA LUGAR:

Model/TypeTotal Time:

Serial Number

Registration Fecha Apertura:

TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 27-30-02Elevator Trailing Edge and Elevator Trim Tab Inspections

EFFECTIVITY

INSPECTION COMPLIANCE

20700001 Thru 20700788 INITIAL 3,000 HRSREPEAT 3,000 HRS

PURPOSETo direct special attention to the area of the elevator trailing edge and trim tab when inspecting the assemblies.Aircraft operation in coastal regions and high humidity areas are prone to have foam deterioration or corrosion.

INSPECTION INSTRUCTIONS1. When inspecting the elevators, pay particular attention to the elevator trailing edge and elevator trim tab. Evidenceof internal skin to foam separation, soft spots, paint blisters, unsealed edges of exposed foam, foam deterioration orcorrosion are cause for replacement of the assembly.

ACCESS/LOCATION DETECTABLE CRACK SIZEElevator N/A

INSPECTION PROCEDUREVisual

REPAIR/MODIFICATIONNot Applicable

COMMENTSRef.: SEB85-7

REMARK COMPLIANCE:

FECHA DE CUMPLIMIENTO ..

MECANICO INSPECTOR

Revision 1: November 1993 (D5121-1-13) 27-30-02


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CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 27-30-02

NOTETrailing edge elevator sections are foamfilled on Model 210-Series aircraft. Elevatorskins are corrugated on Model 206-Seriesaircraft.Beginning in 1968, the Model 206 Seriesuses the Model 210 elevator configuration.This change standardizes 200-Series elevatorStabilizer installations.

Elevator Trailing Edge and Elevator Trim Tab InspectionFigure 3-2

Revision 1: November 1993 (D5121-1-13)

27-30-02


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Aircraft CESSNA LUGAR:


Serial Number


TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 28-30-01

Quick Drain Valves - Fuel Reservoir and Fuel Tanks.

EFFECTIVITYINSPECTION COMPLIANCE

20700001 Thru 20700788 INITIAL 1,000 HRS or 2 YRS

REPEAT 1,000 HRS or 2 YRSThereafter

PURPOSE

To check for possible corrosion.

INSPECTION INSTRUCTIONS1. Remove each fuel reservoir and fuel tank (cell) quick drain and inspect for corrosion. If corrosion appears the

valve must be replaced.2. The reservoir tank should be inspected for internal corrosion also.

ACCESS/LOCATION DETECTABLE CRACK SIZEUnderside of fuselage and wing. N/A


REPAIR/MODIFICATIONReplace as required.

COMMENTSRef: SE84-8

REMARK COMPLIANCE:


MECANICO INSPECTOR



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Quick Drain Valves - Fuel Reservoir and Fuel TanksFigure 3-5



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Serial Number


TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 28-40-01Fuel Gaging Systems




PURPOSEDue to various problems that may occur within the system, the fuel gage may not read empty when the fuel tank is

empty.

INSPECTION INSTRUCTIONS

1. Perform the following inspection every 1000 hours or 3 years or whenever indication of erroneous fuel gagingoperation may occur.

2. De fuel Aircraft.3. Turn master switch on, ensure that the fuel gage reads "0" empty when the tank has only unusable fuel

remaining.

ACCESS/LOCATION DETECTABLE CRACK SIZEWing tank filler port N/A

INSPECTION PROCEDURE

Visual

REPAIR/MODIFICATIONAdjust/replace transmitter and/or gage as required.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR



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Serial Number



Hydraulic Hose Replacement and Hydraulic Component Replacement


20700001 Thru 20700788 INITIAL 5 YRS or ON CONDITION

REPEAT 5 YRS or ON CONDITION

PURPOSE

To ensure that the hydraulic hose and components installed on the airplane are inspected at the proper interval.


1. Refer to SNL85-54 (See excerpts under COMMENTS of this CAP.)

ACCESS/LOCATION DETECTABLE CRACK

As required. N/A


REPAIR/MODIFICATION

COMMENTS

Refer to SNL85-54.The "on condition" interval applies to -- *

* Brake and landing gear hydraulic system hoses of the later synthetic material (S2178-XXX partnumbers).

* Landing gear hydraulic system power packs used on 1979 and later models (9881124-XX).

* All other components except earlier power packs and hoses of rubber material.

Landing gear power packs used prior to 1979 models still require overhaul every 5 years to replace rubbercomponents. All brake and landing gear hydraulic system hoses used prior to the S2178-XXX part numbers stillrequire replacement every 5 years to replace the rubber hose material.



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NOTE

Although part number identification is the positive method to determinehose material, the synthetic hydraulic system hoses generally have a smooth,

somewhat shiny surface texture and are generally a blue or reddish color.Rubber hoses are generally black and have a dull, rougher surface texture.

The new overhaul/replacement requirements will be incorporated in future revisions to the applicable airplane PartsCatalogs and Service Manuals.

The revised requirements in no way preclude the importance of accomplishing thorough hydraulic system inspections,as detailed in the applicable airplane Service Manual. Routine inspections are of the utmost importance to ensurecontinued airworthiness, durability and reliability.

REMARK COMPLIANCE:


MECANICO INSPECTOR




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Serial Number


TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 32-50-02Nose Gear Steering Collar and Upper Torque Link


20700001 Thru 20700788INITIAL 3,000 HRS

REPEAT * 3,000 HRSThereafter

PURPOSEReports of nose gear steering collar cracking as a result of operations in very rough field conditions.In addition the upper torque link becomes seized in the stop boss area resulting in cracks.

INSPECTION INSTRUCTIONS1. If airplane has been or is operated in rough field conditions, the nose gear steering collar should be inspected in

the area of the stop pin for cracking where the cross sectional area of the collar is reduced.2. Use Dye Penetrant to determine if cracks exist in the steering collar and upper torque link.

ACCESS/LOCATION DETECTABLE CRACK SIZE

Nose Gear If part is cracked, replacementis required.

INSPECTION PROCEDURE* Visual and the use of Dye Penetrant at each 1,000 HR if airplane is being used in rough field operation.

REPAIR/MODIFICATIONRemove and replace with a new steering collar P/N 1243811-6. Refer to specific Model Parts Catalog for specialnotes on additional parts required when installing steering collar.

COMMENTSRef: SE71-4

REMARK COMPLIANCE:


MECANICO INSPECTOR




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Nose Gear Steering Collar & Upper Torque LinkFigure 3-9 (Sheet 1 of 2)




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Nose Gear Steering Collar & Upper Torque LinkFigure 3-9 (Sheet 2 of 2)



Model/Type

Total Time:Serial Number



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Engine Compartment Wiring and Equipment Installation

EFFECTIVITY INSPECTION COMPLIANCE



PURPOSEPossible deterioration after an extended period of time.

INSPECTION INSTRUCTIONS1. Inspect all wiring, protective sleeving, clamps, supports, etc. for signs of deterioration due to heat, abrasion

vibration, etc.2. Assure that all wiring is properly supported and is secured in such a manner as not to come in contact with sharp

edges of sheet metal parts, engine controls or engine components that operate at elevated temperatures.3. Inspect all electrical grounds at the firewall for security and corrosion.4. Assure that voltage regulators or alternator control units mounted on the firewall are free of corrosion and are

properly grounded. (Remove bolts and clean.)5. Assure that terminals of sender units on engine are secure and the wiring is free of damage from heat or

abrasion.6. Assure that engine is properly grounded to the airframe.

ACCESS/LOCATION DETECTABLE CRACK SIZERemove engine cowling N/A


REPAIR/MODIFICATION

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




Serial Number



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Fuselage Wing Strut Attach Forging


20700001 Thru 20700788INITIAL 12,000 HRSREPEAT 3,000 HRS

ThereafterPURPOSETo check for possible cracks radiating out of wing strut attach holes and rivet holes attaching end fittings to the struttube. Also, check for loose and working fasteners in forging attachment.

INSPECTION INSTRUCTIONS1. Inspect wing strut attach forging for cracks.2. Visually inspect for loose and working fasteners.3. Eddy Current inspect per instructions in Section 4-0, Basic Information, pages x and xi

ACCESS/LOCATION DETECTABLE CRACK SIZESupport wing and remove strut and fairings. Strut attach hole No Cracks.

Surrounding area - 0.060 detectable cracks.

INSPECTION PROCEDUREEddy Current strut attach hole. Visually inspect remaining areas of the strut attach forging for cracks, loose andworking fasteners.

REPAIR/MODIFICATIONReplace wing strut attach forging if crack(s) radiate out from the attach hole. Contact Cessna for repair of theremaining areas.

COMMENTSReport any cracks or loose/working fasteners to Cessna Aircraft Company.

Should any history of low level overland survey or patrol exist then the initial eddy current inspection and interval shallbe half of the hours listed above.

REMARK COMPLIANCE:


MECANICO INSPECTOR

Temporary Revision Number 1 (D5121-1-13) 53-40-01July 15, 1998



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Aircraft CESSNA LUGAR:Model/Type Total Time:


Fuselage Wing Strut Attach

Forging Figure 3-13

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Serial Number



Fuselage Wing Attachments



ThereafterPURPOSETo inspect wing attach fitting for damage.

INSPECTION INSTRUCTIONS1. Inspect wing attach fittings and their adjacent supporting structure.2. Replace cracked wing attach and fitting bolts.3. Eddy Current inspect per instructions in Section 4-0, Basic Information, pages x and xi.


Remove wing-to-fuselage fairings. N/A

INSPECTION PROCEDUREEddy Current

REPAIR/MODIFICATIONIf cracks are found, contact Cessna Aircraft Company and describe condition.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




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Fuselage Wing AttachmentsFigure 3-14



Model/Type Total Time:


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Serial Number



Fuselage Vertical Fin Attachments



ThereafterPURPOSE

Structural Testing.


1. Visually inspect Sta. 209/239 forward bulkhead and Sta. 230/260 aft bulkhead in the area of the vertical fin sparattachment.

2. Dye Penetrant inspect rudder cable cutouts in Sta. 230/260 aft bulkhead and Sta. 209/239 forward bulkhead.3. Dye Penetrant inspect the upper corners of Sta. 230/260 bulkhead that contain the aft horizontal tail attachment.


Remove vertical fin-to-horizontal tail fairings. Remove stinger 0.06 Inch.Sta 209/239 fwd bulkhead and Sta. 230/260 aft bulkhead.

INSPECTION PROCEDUREVisual and Dye Penetrant

REPAIR/MODIFICATIONContact Cessna and define extent of damage.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




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Fuselage Vertical Fin AttachmentsFigure 3-16 (Sheet 1 of 4)


CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS


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Serial Number



Main Landing Gear Support Fittings


20700001 Thru 20700788 INITIAL 3,000 HRS

REPEAT 1,000 HRSThereafter

PURPOSEOutboard forging has experienced cracking in service.

INSPECTION INSTRUCTIONS1. Visually inspect both inboard and outboard main landing gear support forgings for cracks in radiuses areas or

cracks propagating out of holes in attachment flanges.

ACCESS/LOCATION DETECTABLE CRACK SIZERemove fuselage to main landing gear spring fairing and floorboard N/Ainspection plate between the main landing gear and inboard forgings.Location/Outboard and inboard MLG support forgings.


Visual

REPAIR/MODIFICATION

Replace

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




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Main Landing Gear Support ForgingsFigure 3-18




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Serial Number



Horizontal Stabilizer Aft Attach Bracket


20700001 Thru 20700788INITIAL 1,000 HRS

REPEAT 200 HRSThereafter

PURPOSECracking has been experienced in the radius areas and the attach points of the bracket flanges on several high timeairplanes.Ref.: SE84-17, FAA AC 43-16 Number 61, Aug. 1983.FAA AC. 43-16 Number 79, Feb. 1985.

FAA AC. 43-16 Number 27, Oct. 1980.FAA AC. 43-16 Number 15, Oct. 1979.


Visually inspect the stabilizer aft spar attach bracket per SE84-17.

ACCESS/LOCATIONDETECTABLE CRACK SIZE

Remove horizontal stabilizer-to-fuselage fairings and stinger. N/A


REPAIR/MODIFICATIONReplacement Per SE 84-17

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




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IMPROVED STEEL BRACKETS (P/N 1232624-1) ARE AVAILABLEFOR THE FOLLOWING SERIALS:20700001 Thru 20700784 (1969 Thru 1984)U206-0915 Thru U20606832 (1968 Thru 1984)

Horizontal Stabilizer Attach BracketFigure 3-19



Model/TypeTotal Time:Serial Number


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Vertical Tail Fin Fuselage Attachments


20700001 Thru 20700021 INITIAL 12,000 HRSREPEAT 6,000 HRS

Thereafter

PURPOSEStructural Testing.

INSPECTION INSTRUCTIONS1. Visually inspect Sta. 209/239 forward fin spar attachment and Sta. 230/260 aft fin spar attachments.2. Dye Penetrant inspect rear spar outboard flanges on inside surface (just above Sta. 230/260 aft bulkhead) at the

lower fwd skin attach rivet holes.


Remove vertical fin-to-horizontal tail fairings. 0.012 Inch.Remove stinger.Sta. 209/239 fwd bulkhead fin spar attachment andSta. 230/260 aft bulkhead fin spar attachment.

INSPECTION PROCEDUREVisual and Dye Penetrant

REPAIR/MODIFICATION

Contact Cessna Aircraft Company and define extent of damage.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




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AFN FIN SPAR ATTACHMENTVertical Tail Fin Fuselage Attachments

Figure 3-20 (Sheet 1 of 5)

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CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS : 55-30-01


Vertical Tail Fin Fuselage AttachmentsFigure 3-20 (Sheet 2 of 5)

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Vertical Tail Fin Fuselage AttachFigure 3-20(Sheet 3 of 5)




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Vertical Tail Fin Fuselage AttachmentsFigure 3-20(Sheet 4 of 5)




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Vertical Tail Fin Fuselage AttachmentsFigure 3-20(Sheet 5 of 5)




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Serial Number


TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 57-10-031. 1222105-37 Stiffener - Front Spar Splice LH - Aft2. 0721402-5 Stiffener - Front Spar Splice LH - Aft3. 1222105-3 Web - Front Spar Splice LH - Aft4. 1222105-5 Web - Front Spar Splice LH - Fwd5. Strut Attach Hole


20700001 Thru 20700788INITIAL 15,000 HRS*REPEAT 3,000 HRS *

PURPOSEStructural Testing.

INSPECTION INSTRUCTIONS1. Eddy Current Inspect the cross-section of the front spar stiffener angle the complete length (6).

(Refer to step 6 for Eddy Current equipment.)2. Eddy Current Inspect the cross-section of the front spar stiffener cap angle the complete length (1).

(Refer to step 6 for Eddy Current equipment.)3. Eddy Current Inspect the lower 1/3 cross-section of the web splice the complete length (2).

(Refer to step 6 for Eddy Current equipment.)4. Eddy Current Inspect the lower 1/3 cross-section or web splice the complete length (3).

(Refer to step 6 for Eddy Current equipment.)5. Eddy Current Inspect strut attach hole. (Refer to step 6 for Eddy Current equipment.)6. Eddy Current inspect per instructions in Section 4-0, Basic Information, pages x and xi.

ACCESS/LOCATION DETECTABLE CRACK SIZEW.S. 100 inspection plates - inspect both wings. 1, 2, 3, & 4 - .12 Inch.Support wing and remove strut. 5 - .06 Inch.


REPAIR/MODIFICATIONRemove and replace.

COMMENTS

Report any cracks to Cessna.* Should any history of low level overland survey and patrol exist then the initial inspection compliance is 8000 hrs.and at 1500 hour intervals thereafter.




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NOTE: REMOVE INSPECTIONPLATE FOR CLARITY

Wing Station 100 Splice Inspection AreaFigure 3-22



Model/TypeTotal Time:Serial Number


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1. 1222005-7 Stiffener - Front Spar Splice LH - Aft2. 0721402-5 Stiffener - Front Spar Splice LH - Aft3. 1222005-3 Web - Front Spar Splice LH - Aft4. 1222005-5 Web - Front Spar Splice LH - Fwd5. Strut Attach Hole

EFFECTIVITY INSPECTION COMPLIANCE

20700001 Thru 20700788 INITIAL 15,000 HRS*

REPEAT 3,000 HRS *

PURPOSE

Structural Testing.

INSPECTION INSTRUCTIONS1. Eddy Current Inspect the cross-section of the front spar stiffener angle the complete length (6).

(Refer to step 6 for Eddy Current equipment.)2. Eddy Current Inspect the cross-section of the front spar stiffener cap angle the complete length (1).

(Refer to step 6 for Eddy Current equipment.)3. Eddy Current Inspect the lower 1/3 cross-section of the web splice the complete length (2).

(Refer to step 6 for Eddy Current equipment.)4. Eddy Current Inspect the lower 1/3 cross-section or web splice the complete length (3).

(Refer to step 6 for Eddy Current equipment.)5. Eddy Current Inspect strut attach hole. (Refer to step 6 for Eddy Current equipment.)6. Eddy Current inspect per instructions in Section 4-0, Basic Information, pages x and xi.


W.S. 100 inspection plates - inspect both wings. 1, 2, 3, & 4 - 0.12 Inch.Support wing and remove strut. 5 - 0.06 Inch.

INSPECTION PROCEDUREEddy Current and/or Radiographic

REPAIR/MODIFICATIONRemove and replace.

COMMENTS

Report any cracks to Cessna.* Should any history of low level overland survey and patrol exist then the initial inspection compliance is 8,000 hrs.and at 1,500 hour intervals thereafter.




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NOTE: WITH THE ADDITION OF ITEM (6) THE FIRST SIGNIFICANT TESTSPECIMEN CRACKS WERE LOCAL SKIN CRACKING(5) AND A CRACK IN ITEM (6)

(CRACKS NOT SHOWN IN ITEMS 5 AND 6).

Wing Station 100 Splice Inspection AreaFigure 3-24

REMARK COMPLIANCE:


MECANICO INSPECTOR

Revision 1 : November 1993 (D5121-1-13) 57-10-04


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Serial Number



Wing Fuselage Attach Fittings



Thereafter

PURPOSEPrimary load path.No known history of cracking except for rear spar web referred to in CAP Item 57-10-05.

INSPECTION INSTRUCTIONS1. Inspect for possible cracking from wing attachment holes outward, (Refer to step 4.).2. Possible galling or deformation of wing attachment holes, (Refer to step 4.).3. Do not remove wing attach bolts unless cracking or looseness suspected, (Refer to step 4.).4. Eddy Current inspect per instructions in Section 4-0, Basic Information, pages x and xi.

ACCESS/LOCATION DETECTABLE CRACK SIZERemove wing-to-fuselage fairing strips. N/A


REPAIR/MODIFICATIONRear Spar Kits Available - Refer to Service Bulletin List in Section I.

COMMENTS

Replace cracked parts.Contact Cessna Aircraft Company for instructions on oversize holes.




7/30/2019 CAP 207 Series

65/67

CAPMODEL 207 SERIES


Wing Fuselage Attach FittingsFigure 3-26

REMARK COMPLIANCE:


MECANICO INSPECTOR



Model/Type

Total Time:Serial Number



7/30/2019 CAP 207 Series

66/67

7/30/2019 CAP 207 Series

67/67

CAPMODEL 207 SERIES



DEJADO EN BLANCO

cap 207 series

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