cap 206 series

CAPMODEL 206 SERIES

SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM

MODEL 200SERIES PISTON

SINGLE ENGINE AIRCRAFT

PROGRAMADE AERONAVEGABILIDAD CONTINUADA

CAP

CARATULA

AUTOR: MELQUIADES CHAVEZ GALDOS

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

CAPMODEL 206 SERIES


PROGRAMADE AERONAVEGABILIDAD CONTINUADA

CAP

MANUAL Nº

REVISION Nº

ASIGNADO A:

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

ORIGINAL

CAPMODEL 206 SERIES


INDICE GENERAL

LISTA DE CONTENIDO PAGINA

CARÁTULA DEL MANUAL 1

CARATULA DE ASIGNACION DEL MANUAL 2

INDICE GENERAL 3 al 5

APLICABILIDAD 6

LISTA DE PAGINAS EFECTIVAS 7 al 9

Página en blanco 10

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

A.1 INTRODUCCIÓN 11

A.2 POLITICA 11

A.3 OBJETIVO 11

A.4 ORGANIGRAMA 12


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 REVISIÓN 15

B.5 REGISTRO DE REVISIONES 16


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) SSD’S 19

2.1 FUNDAMENTOS USADOS PARA SELECCIONAR LOS SSD´s 19

2.2 LOS SSD´s FUERON SELECCIONADOS BASADOS EN LO SIGUIENTE 19

A. EXPERIENCIA EN EL SERVICIO 19

INDICE GENERAL (Cont....)

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

CAPMODEL 206 SERIES



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


SECTION II - LISTING OF CONTINUED AIRWORTHINESS PROGRAM INSPECTIONS 29- 30

INDICE GENERAL (Cont....)



CAPMODEL 206 SERIES


SECTION III – CONTINUING AIRWORTHINESS PROGRAM INSPECTION 31

27-30-01 Trim TabActuator Mounting Bracket (R.H. Stabilizar) 31-32

27-30-02 Elevator Trailing Edge andTrim Tab Inspections 33-34

28-20-02 Hose – Fuel Vent 35-36

28-30-01 Quick Drain Valves – Fuel Reservoir and Fuel Tanks 37-38

28-40-01 Fuel Gauging Systems 39

29-10-01 Hydraulic Hose Replacement and Hydraulic Component Replacement 40-41

32-50-01 Nose Gear Turning Stop 42-43

32-50-02 Nose Gear Steering Collar and Upper Torque Link 44-46

39-00-01 Engine Compartment Wiring and Equipment Installation 47

53-10-02 Fuselage Fwd Doorpost At Lower Corner of Windshield 48-49

53-40-01 Fuselage Wing Attachments 50-51

53-40-02 Fuselage Wing Attachments 52-53

53-40-04 Fuselage Vertical Fin Attachments 54-58

53-40-06 Main Landing Gear Fittings 59-60

55-10-01 Horizontal Stabilizer Aft Attach Bracket 61-62

55-30-01 Vertical Tail Fin Fuselage Attachments 63-68

57-10-02 Front Spart Splice LH 69-70

57-10-03 Front Spar Splice LH – Aft 71-72

57-10-04 Front Spar Splice LH – Aft 73-74

57-10-05 rear Wing Spar Web - Inboard 75-76

57-10-06 Wing Fuselage Attach Fittings 77-78

57-10-07 Wing Strut 79-80

57-10-11 Wing Strut Tube 81

57-50-02 Aileron Hinge Bracket 82-83



CAPMODEL 206 SERIES


APLICABILIDAD

MODEL YEAR SERIAL

U206/TU206 1966 THRU 1969 U206-0438 THRU U206-1444U206/TU206 1970 THRU 1986 U20601445 THRU U20607020

OB-1616 AÑO DE FABRICACION 1967 SERIAL NUMBER U2060878

OB-1192 AÑO DE FABRICACION 1980 SERIAL NUMBER 20605538

OB-1204 AÑO DE FABRICACION 1980 SERIAL NUMBER 20605800


CAPMODEL 206 SERIES


LISTA DE PÁGINAS EFECTIVAS

PAGINA REVISION FECHA

1 ORIGINAL 08-ABR-2010






























CAPMODEL 206 SERIES


LISTA DE PÁGINAS EFECTIVAS (Cont…)
































CAPMODEL 206 SERIES


LISTA DE PÁGINAS EFECTIVAS (Cont…)




























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

CAPMODEL 206 SERIES


PAGINA INTENCIONALMENTEDEJADO EN BLANCO

A.0 PROGRAMA DE AERONAVEGABILIDAD CONTINUADA (CAP)


CAPMODEL 206 SERIES


A.1 INTRODUCCIÓN

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

Este Manual será usado por TRAVEL AIR como parte de su Programa de Mantenimiento, para garantizar la Aeronavegabilidad continuada de sus Aeronaves. los ICA (Inspecciones de aeronavegabilidad Continuada) son fichas de inspección donde se muestran los cumplimientos INICIAL y REPETITIVO .

A.2 POLITICA

TRAVEL AIR E.I.R.L., posee un equipo de trabajo de alto nivel profesional cuyas acciones diarias de mantenimiento las ejecutamos con un elevado profesionalismo para garantizar la aeronavegabilidad continua de nuestras aeronaves, nuestra visión de empresa está basada en los siguientes principios:

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

CREATIVIDAD E INNOVACIÓN como parte de nuestro reto diario para el mejoramiento continúo.

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

CONSCIENCIA en la ejecución de tareas de mantenimiento libre de errores y el COMPROMISO leal con la compañía y con las realizaciones de calidad.

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

A.3 OBJETIVO.

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

A.4 ORGANIGRAMA


CAPMODEL 206 SERIES


Este organigrama obedece únicamente a los responsables directos de velar el cumplimiento del Programa de Aeronavegabilidad Continua (CAP).


GERENTE DE MANTENIMIENTOGERENTE DE MANTENIMIENTO

JEFE DE CONTROL DE CALIDAD

JEFE DE CONTROL DE CALIDAD

INSPECTOR DE MANTENIMIENTO ICA

INSPECTOR DE MANTENIMIENTO ICA

CONTROL DE MANTENIMIENTO

CONTROL DE MANTENIMIENTO

INSPECTOR DE MANTENIMIENTO

NAZCA

INSPECTOR DE MANTENIMIENTO

NAZCA

SUPERVISOR DE MANTENIMIENTO ICA

SUPERVISOR DE MANTENIMIENTO ICA

SUPERVISOR DE MANTENIMIENTO

NAZCA

SUPERVISOR DE MANTENIMIENTO

NAZCA

CAPMODEL 206 SERIES



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

B.1 CARATULA DEL PROGRAMA

Es la primera página de este Programa con el propósito de facilitar su identificación.

B.2 CARATULA DE ASIGNACION DEL PROGRAMA


CAPMODEL 206 SERIES


Es la Segunda Pagina de este Programa donde se registra el Numero del Manual asignado, el Número de Revisión actual y el nombre del departamento, entidad o a quien es asignado el presente el manual.

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

Los Programa asignados serán numerados correlativamente con un número de control. El departamento de Control de Mantenimiento mantendrá una Lista de Asignación de los Manuales en la que incluirá el número de control y las revisiones que se han incorporado.

01 Dirección General de Aeronáutica Civil (D.G.A.C.) (CD)

02 Gerencia de Mantenimiento

03 Departamento de Control de Calidad

04 Control de Mantenimiento

05 Estación de Línea Nazca

06 Departamento de Instrucción y Publicaciones

B.4 APROBACION Y REVISIÓN

En esta sección se establecen los procedimientos para que el CAP (Programa de Aeronavegabilidad Continuada) se mantenga actualizado.

La revisión del CAP, es responsabilidad directa del Gerente de Mantenimiento, sin embargo podrá delegar esta función; toda vez que la DGAC emita una nueva Norma técnica, revisiones efectuadas por Cessna o cuando Travel Air considere conveniente para mejorar su Programa.


CAPMODEL 206 SERIES


El responsable de efectuar la revisión recibirá todas las sugerencias de revisiones al manual de los usuarios asignados, insertando las correcciones o modificaciones que considere necesarias; una vez realizada la revisión se insertara al el pie de página la fecha de la revisión seguido del N de revisión correspondiente, para posteriormente solicitar a través del Inspector Principal de Mantenimiento (IPM DGAC) su aceptación o aprobación.

El responsable de la revisión remitirá al IPM de Travel Air, a través de mesa de partes del MTC, una carta de presentación con el logo tipo de la compañía y la firma del Gerente de Mantenimiento junto con un ejemplar de las páginas revisadas y dos copias de la lista de páginas efectivas.

Una vez aprobada o aceptada la revisión, con la refrenda del IPM en la lista de las páginas efectivas, el Departamento de Control de Mantenimiento sacará copias suficientes de las revisiones para su distribución a las diferentes áreas.

Las revisiones serán distribuidas por el encargado del Departamento de Control de Mantenimiento con un cargo de entrega, será responsabilidad del usuario el insertar las revisiones de acuerdo con la lista de páginas efectivas.

B.5 REGISTRO DE REVISIONES

REVISIONFECHA DE REVISION

FECHA DE APROBACION

EFECTUADO POR

ORIGINAL 08-05-2010 CARLOS PALACIN CORCUERA


CAPMODEL 206 SERIES



CAPMODEL 206 SERIES



INTRODUCCION AL PROGRAMA DE AERONAVEGABILIDAD CONTINUADA

1.0 DISCUSION.

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

1.1 INTRODUCCION AL CAP.


CAPMODEL 206 SERIES


Las aeronaves que contenidas en este CAP, fueron entregados (cuando fueron vendidos) con los programas de inspección recomendadas. Manuales de mantenimiento continuamente actualizados complementados con los boletines del servicio e información para el propietario fueron proporcionados (mediante subscripciones con Cessna) con la intención de mantener la aeronavegabilidad de las aeronaves.

Debido a que estas aeronaves han sido asignados a variadas misiones (vuelos privados, turísticos, paracaidismo etc.), el tipo de cuidado que se le presta, así como el envejecimiento general e índice de uso (horas de vuelo del avión), Cessna considera necesario proporcionar requerimientos adicionales a los programas de inspección como un medio de garantía adicional para que los aviones puedan continuar siendo aeronavegables. De la experiencia que Cessna ha adquirido y el apoyo continuo de los reportes de campo de las aeronaves, Cessna continúa dando información de servicio para las aeronaves por medio de los CAP.

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

El CAP no intenta hacer cambios o sustituir, pero puede proporcionar información adicional al MANUAL DE MANTENIMIENTO, boletines de servicio o cartas de servicio que son aplicables.

1.2 OBJETIVO DEL CAP.

Este CAP se ha desarrollado para asegurar la capacidad de la aeronave para performar dentro de los parámetros de la certificación original.

Los CAP están direccionados hacia los componentes estructurales primario y secundario, motor, Items eléctricos y sistemas primario y secundario para lograr este objetivo declarado de aeronavegabilidad continuada.

Condiciones para establecer las bases para que los Items detallados 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 está dirigido a un componente o parte específico, se da a entender que la inspección incluirá la observación y evaluación de las aéreas alrededor de las partes y equipamientos. Cualquier discrepancia encontrada durante la inspección fuera del alcance del CAP deberá ser comunicado a Cessna a través del sistema de reporte de condición existente de manera que se pueden realizar cambios al CAP en caso necesario.

C. Los aviones modificados por un Certificado Tipo Suplementario (STC) no son responsabilidad de Cessna. Cualquier inspección requerida dentro de lo manuales de Cessna o CAP´s que tengan áreas que hayan sido modificados por un STC serán automáticamente referidas al titular del STC, por el propietario y / u organización de mantenimiento para la obtención de las directrices de mantenimiento aprobadas por la FAA.

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


CAPMODEL 206 SERIES


Los elementos designados para la inspección en este documento son esas estructuras o sistemas que incluyen el motor y eléctricos cuyos fallas podrían causar la pérdida o daños sustanciales a la aeronave. Los términos detalles estructuralmente importantes o detalles importantes del sistema (SSD) se aplicará a estos Items críticos. La selección y el seguimiento de estos SSD´s es el núcleo del (CAP) Programa de Aeronavegabilidad continuada.

2.1 FUNDAMENTOS USADOS PARA SELECCIONAR LOS SSD'S.

La flota Cessna series 200 fue diseñada para vuelos comerciales y vuelos de placer. Sin embargo, desde su producción en común algunos de estos aviones tienen más de 10.000 horas de vuelo y otros son mayores de (20 años) con pocas horas de vuelo, los métodos y fundamentos utilizados para la selección de los SSD críticos se dispone en el párrafo 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 condición también fueron revisados durante el proceso de selección de los SSD´s críticos. Los informes (reportes) también fueron utilizados para seleccionar los items que eran similares en aplicación para otras aeronaves basadas en función a su diseño y carga.

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

Los boletines de servicio han sido revisados y volvieron a tratarse los criterios de seguridad de vuelo para ayudar a seleccionar los SSD críticos. Algunos de estos documentos se consideran vitales para la operación segura de la aeronave y en consecuencia, la estructura afectada o componentes del sistema serán enumerados como un SSD.

NOTA.Algunos de estos boletines pueden ya estar incorporados dentro del programa de mantenimiento del operador.

C. ANALISIS.

Se revisaron los análisis existentes para identificar los componentes en áreas que puedan haber mostrado el potencial requerimiento de inspección adicional.

D. PRUEBAS.

Se realizo una revisión de los resultados de las pruebas aplicables al diseño. Se evaluaron los resultados de las condiciones de carga junto con pruebas estáticas y de fatiga. Los datos resultantes se utilizaron para determinar si el componente debería ser considerado como un SSD para su incorporación dentro del CAP.

E. INSPECCION DEL AVION.


CAPMODEL 206 SERIES


Aeronaves con muchos años de operación fueron desarmadas completamente para ser inspeccionado con la finalidad de seleccionar los SSD. Inspecciones especiales fueron realizadas a otras aeronaves con muchos años de operación para complementar estas inspecciones.

Los efectos de la corrosión no se han tenido en cuenta en la selección y justificación del SSD o los efectos sobre la fatiga por estrés. Es difícil determinar los efectos de la corrosión, pero como son recibidos los reportes de inspección del CAP, los tiempos de inspección serán ajustados como sea necesario dependiendo de la severidad de la discrepancia.

NOTA

Si una aeronave tiene un historial donde se hayan realizado vuelos de reconocimiento 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 éxito en forma permanente, es esencial que exista un libre flujo de información entre el operador, la DGAC y Cessna. Los detalles significativos de los resultados de la inspección, reparaciones y modificaciones ejecutados deben ser comunicados a Cessna con el fin de evaluar la eficacia de sus procedimientos de control recomendadas y los intervalos de tiempo. En algunos casos, es posible obtener extensiones en las frecuencias de inspección si la información obtenida sugiere la aparición de problemas de fatiga a un mayor número de horas de vuelo de lo inicialmente previsto.

Además, Items no considerados anteriormente para su inclusión en el CAP pueden ser descubiertos por el operador a través de las inspecciones y los reportes de inspección. Estos Items serán evaluados por Cessna y si es de aplicación general a las configuraciones de la aeronave en cuestión, se añadirá al CAP para el beneficio de todos.

Se ha establecido e incorporado en este documento un sistema de reporte consecuente con los sistemas empleados por el CESSNA PROPELLER PRODUCT SUPPORT ORGANIZATION y registrada en este CAP. Las copias de los formularios pertinentes están disponibles para usted en la Estación de Servicio de Cessna o el Servicio de Ingeniería de campo de la Fábrica.

3.1. REPORTANDO LAS DISCEPANCIAS.

El reporte de las discrepancias es esencial para proveer y ajustar los parámetros de inspección y los intervalos de tiempo en mayor o menor intensidad, así como la incorporación o eliminación de los SSD. Basado en los datos reportados, puede ser posible perfeccionar los métodos de inspección, reparaciones y modificaciones involucrados en los SSD.


CAPMODEL 206 SERIES


Todas las rajaduras y corrosiones de gravedad encontrados en materia de inspección de un SSD serán notificadas a la Cesnna. Los resultados de la inspección SSD se informara en un formulario como se muestra en la página siguiente:

3.2. DISPOSICION DEL FORMATO DE DISCREPANCIAS.Enviar todos los datos disponibles incluyendo las reparaciones, fotos, etc. a la siguiente dirección:

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 condición de comunicación del sistema de reportes para aquellos Items no cubiertos por el CAP.

3.3. ACCIONES DE SEGUIMIENTO DEL FABRICANTE.

Todos los reportes SSD serán revisados para ver si algunas de las siguientes acciones deberían ser tomadas:

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

2. Chequear otras aeronaves con altas cantidad de horas a fin de considerar la emisión de un boletín de Servicio.

3. Ver si un reforzamiento es necesario.

4. Revisar el CAP si es necesario.

4.0. INFORMACION BASICA.

Este CAP aplica a los aviones Series 200. Refiérase a los manuales de Servicio/Mantenimiento individuales de la serie 200 para los específicos programas de inspección de su aeronave.


CAPMODEL 206 SERIES


NOTA.- Desde el párrafo 4.1 hasta la página final se mantendrán tal como fueron publicados 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 for detecting damage, then it will be considered as a possible alternate inspection method.

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 the simulated cracks in a bolt hole and surface reference standard equivalent to the HRS-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 the surface which may not be evident by normal visual inspection. Penetrant inspection can be used on most airframe parts and assemblies accessible for its application. The inspection is performed by applying a liquid which penetrates into surface defects so that visual indications are obtained by color contrast or fluorescence of the penetrant under the display of black light. The penetrant method of inspection requires that the surface in the inspection area be thoroughly clean and free of paint.

2. MATERIALS AND EQUIPMENT

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

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

Equipment Manufacturer

ZA 43 Fluorescent Penetrant Kit Magnaflux Corporation contains the following: 7300 W. Lawrence

Avenue Chicago, IL 60656ZL-22A Penetrant


CAPMODEL 206 SERIES


ZP-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 any contaminants which would mask or close a defect open to the surface. The surface should be dry before applying the penetrant.

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

(2) The penetrant materials and the area to be tested shall have a temperature of 60°F to 130°F

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 penetrant from 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 penetrant cleaner. Do not flush surface with penetrant cleaner as this will flush penetrant from 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 thickness possible..The best results are obtained by a very thin coating. The Film of developer should be slightly translucent. When applying dry power developer, thoroughly dust area, then blow off excess power. When applying nonaqueous wet developer from a pressurized can, spray a thin coat on the surface and allow to dry in ambient air. The developer liquid shall be agitated frequently to prevent settling of the solid particles in the liquid vehicle. The full dwell time after developer has been applied should be no less than 5 minutes.

E. Interpretation of Indications.

(1) An 8X magnifying glass should be used to examine area unless indications are visible to the naked eye. Any surface break will be revealed by fluorescent indication on a blueish background. A fluorescent line will indicate a crack and will be sharply defined at first and the amount of bleeding gives a clue to the depth of the crack. Inspectors should watch indications grow, since the first sharp


CAPMODEL 206 SERIES


indications tell much of the nature of the defect, and the amount of bleeding gives information as to the extent. A deep discontinuity indication will reappear a number of times when wiped clean and developer reapplied.

4.2. MANUALS.

Cessna has a number of documents that are useful to maintaining continued airworthiness 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 to these 200 Series Aircraft CAPS, are listed in Section 1, titled: TECHNICAL DOCUMENT REFERENCE. For information concerning the technical data included in these Service Letters/Bulletins that apply to your aircraft, you may contact Cessna's Propeller Technical Information Services, Department 753. The telephone number for customer 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 from Cessna. 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 accomplished under STC's by other organizations without Cessna Engineering involvement. Because Cessna does not have knowledge of the airworthiness of STC's, this report cannot apply to those areas affected by such STC's and the STC holder should prepare a CAP for each particular modification.

6.0. SIGNIFICANT DETAILS.

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


CAPMODEL 206 SERIES


A summary of the CAPs is shown in the section titled: LISTING OF CONTINUED AIRWORTHINESS 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/Maintenance Manual or FAA AC43-13 acceptable methods of alteration and repair. Any repair not covered by the recommendations in this CAP Program may be coordinated with Cessna Technical Information Services at Telephone (316) 941-8500/Fax (316) 942-6000

CESSNA AIRCRAFT COMPAINYMODEL 200 SERIES

CONTINUED AIRWORTHINESS PROGRAM

DISCREPANCY REPORT

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

AIRPLANE:_________


CAPMODEL 206 SERIES


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

SECTION I - TECHNICAL DOCUMENT REFERENCE

SERVICE MANUALS

Model Number Title

205, 206, and 210 (1960 - 1965) D470-13 200 Series206 and 210 (1966 - 1968) D606-1-13 200 Series


CAPMODEL 206 SERIES


206 and T206 (1969 - 1976) D2007-3-13 206 and T206 Series206 and T206 (1977 - 1986) D2070-2-13 206 and T206 Series

To obtain Service Manuals, write to:Cessna Aircraft Company Supply DivisionAtt: SPA DeptP.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 32-60-01SE84-8 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


CAPMODEL 206 SERIES



SECTION II - LISTING OF 206 SERIES CONTINUED AIRWORTHINESS PROGRAM INSPECTIONS

OB-1616 AÑO DE FABRICACION 1967 SERIAL NUMBER 2060878OB-1192 AÑO DE FABRICACION 1980 SERIAL NUMBER 20605538OB-1204 AÑO DE FABRICACION 1980 SERIAL NUMBER 20605800

ContinuedAirworthiness

Program Inspection

Inspection ComplianceNumber

Title

DateInitial

Effectivity INITIAL REPEAT


CAPMODEL 206 SERIES


27-30-01Trim Tab Actuator Mounting

Bracket R.H. (Stabilizer)U206-0276 Thru U20602199

1,000 Hrs

or 3 Yrs

1,000 Hrsor 3 Yrs

27-30-02Elevator Trailing Edge and

Trim Tab InspectionsU206-0915 Thru U20606889

3,000Hrs

3,000Hrs

28-20-02 Hose - Fuel Vent U200276 Thru U20607020 5 Yrs 5 Yrs

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

U206-0276 Thru U206070201,000 Hrs

or 2 Yrs

1,000 Hrsor 2 Yrs

28-40-01 Fuel Gauging Systems U206-0276 Thru U206070201,000 Hrs

or 3 Yrs

1,000 Hrsor 3 Yrs

29-10-01Hydraulic Hose Replacement

and Hydraulic ComponentReplacement

U206-0276 Thru U206070205 Yrs or

OnCondition

5 Yrs orOn

Condition

32-50-01 Nose Gear Turning Stop U206-0276 Thru U206070203,000Hrs

1,000Hrs

32-50-02Nose Gear Steering Collar

and Upper Torque LinkU206-0276 Thru U20607020

3,000Hrs

3,000Hrs

39-00-01Engine Compartment Wiringand Equipment Installation

U206-0276 Thru U206070206,000Hrs

or 5 Yrs

2,000Hrs

or 2 Yrs

53-10-02Fuselage Fwd Doorpost At

Lower Corner OfWindshield

U206-0273 Thru U206070204,000Hrs

4,000Hrs

53-40-01Fuselage Wing Strut Attach

ForgingU206-0276 Thru U20607020

12,000Hrs

1,000Hrs

53-40-02 Fuselage Wing Attachments U206-0276 Thru U2060702012,000

Hrs2,000Hrs

53-40-04Fuselage Vertical Fin

AttachmentsU206-0276 Thru U20601905

12,000Hrs

2,000Hrs

53-40-06 Main Landing Gear Fittings 206-0001 Thru U206070203,000Hrs

1,000Hrs

55-10-01Horizontal Stabilizer Aft Attach

BracketU206-0276 Thru U20607020

1,000Hrs

200Hrs

55-30-01Vertical Tail Fin Fuselage Attachments

206-0001 Thru U206-01905 12,000

Hrs6,000 Hrs

57-10-02

1. 0721402-3 Angle - Front Spar Splice LH 2. 0721400-13 Channel - Front Spar Splice LH3. 0721400-17 Plate - Front Spar Splice LH 4. Strut Attach Hole

206-0001 Thru 206-0275U206-0276 Thru U20601700

P206-0001 Thru P2060064712,000

Hrs2,000 Hrs

LISTING OF CONTINUED AIRWORTHINESS PROGRAM INSPECTIONS (Cont…)

ContinuedAirworthiness

Program Inspection

Inspection ComplianceNumber

TitleDate Initial Effectivity INITIAL REPEAT

57-10-03 1. 1222105-37 Stiffener - Front Spar Splice LH - Aft2. 0721402-5 Stiffener - Front

U20601701 Thru U20604649 15,000Hrs

3,000Hrs


CAPMODEL 206 SERIES


Spar Splice LH - Aft.3. 1222105-3 Web - Front Spar Splice LH - Aft4. 1222105-5 Web - Front Spar Splice LH - Fwd5. Strut Attach Hole

57-10-04

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

U20604645 Thru U20607020

15,000 Hrs

3,000 Hrs

57-10-05 Rear Wing Spar Web- Inboard U206-0276 Thru U206017003,000Hrs

1,000Hrs

57-10-06 Wing Fuselage Attach Fittings U206-0276 Thru U2060702012,000

Hrs3,000 Hrs

57-10-07 Wing Strut 206-0001 Thru U2060170012,000

Hrs3,000 Hrs

57-10-11 Wing Strut Tube U206-0276 Thru U206070201,000 Hrs

1,000 Hrs

57-50-02 Aileron Hinge Bracket U206-0276 Thru U206070202,500Hrs

2,500Hrs

SECTION III - CONTINUING AIRWORTHINESS PROGRAM INSPECTION

Aircraft CESSNA LUGAR:

Model/TypeTotal Time:

Serial Number

Registration Fecha Apertura:

TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 27-30-01Trim Tab Actuator Mounting Bracket (R.H. Stabilizer)


CAPMODEL 206 SERIES

SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAMEFFECTIVITY

INSPECTION COMPLIANCE206-0001 Thru 206-0275P206-0001 Thru P20600647 INITIAL 1000 HRS or 3 YRSU206-0276 Thru U20602199 Whichever Occurs First

REPEAT 1000 HRSWhichever Occurs First or 3 YRSThereafter

PURPOSEIf actuator mounting bracket is cracked completely through, stability can be lost and could cause control instability of aircraft.

INSPECTION INSTRUCTIONS1. Inspect 1232139-1 bracket assembly in area as shown on page 32

ACCESS/LOCATION DETECTABLE CRACK SIZERemove trim actuator cover plate on lower right-hand N/Aside on horizontal stabilizer.

INSPECTION PROCEDUREVisual

REPAIR/MODIFICATIONReplace bracket if cracked.

COMMENTSRef: SEB85-5

REMARK COMPLIANCE:

FECHA DE CUMPLIMIENTO ……………………………………………………………..

MECANICO INSPECTOR

Revision 1: November 1993 (D5121-1-13) 27-30-01

CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 27-30-01


CAPMODEL 206 SERIES


Trim Tab Actuator Mounting Bracket (R.H. Stabilizer)Figure 3-1




Serial Number



CAPMODEL 206 SERIES


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

EFFECTIVITY

P206-0420 Thru P20600647 INSPECTION COMPLIANCEU206-0915 Thru U20606889

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. Evidence of internal skin to foam separation, soft spots, paint blisters, unsealed edges of exposed foam, foam deterioration or corrosion are cause for replacement of the assembly.

ACCESS/LOCATION DETECTABLE CRACK SIZEElevator N/A


REPAIR/MODIFICATIONNot Applicable

COMMENTSRef.: SEB85-7

REMARK COMPLIANCE:


MECANICO INSPECTOR




CAPMODEL 206 SERIES


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 elevator Stabilizer installations.

Elevator Trailing Edge and Elevator Trim Tab InspectionFigure 3-2




Serial Number


CAPMODEL 206 SERIES



TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 28-20-02

Hose - Fuel Vent

EFFECTIVITY

206-0001 Thru 206-0275 INSPECTION COMPLIANCEU200276 Thru U20607020P206-0001 Thru P20600647 INITIAL 5 YRS

REPEAT 5 YRSThereafter

PURPOSETo ensure hose integrity.

INSPECTION INSTRUCTIONS1. Check hoses on each side of airplane for cracks, weeping, and deterioration.2. Replace hose as necessary.3. When replacing hoses, use new clamps.

ACCESS/LOCATION DETECTABLE CRACK SIZEAccess plate Just outboard of fuel tank on the bottom side of wing. N/A


REPAIR/MODIFICATIONReplace as required.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




CAPMODEL 206 SERIES


Hose - Fuel VentFigure 3-3




Serial Number



CAPMODEL 206 SERIES



Quick Drain Valves - Fuel Reservoir and Fuel Tanks.

EFFECTIVITY INSPECTION COMPLIANCE

206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 1,000 HRS or 2 YRSP206-0001 Thru P20600647

REPEAT 1,000 HRS or 2 YRS Thereafter

PURPOSETo 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




CAPMODEL 206 SERIES


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




Serial Number



CAPMODEL 206 SERIES


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


206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 1,000 HRS or 3 YRSP206-0001 Thru P20600647


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 gaging operation 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


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

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




Serial Number



CAPMODEL 206 SERIES



Hydraulic Hose Replacement and Hydraulic Component Replacement

EFFECTIVITYINSPECTION COMPLIANCE

206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 5 YRS or ON CONDITIONP206-0001 Thru P20600647

REPEAT 5 YRS or ON CONDITION

PURPOSETo 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

INSPECTION PROCEDURE

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 part numbers).

* 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 rubber components. All brake and landing gear hydraulic system hoses used prior to the S2178-XXX part numbers still require replacement every 5 years to replace the rubber hose material.



NOTE


CAPMODEL 206 SERIES


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 Parts Catalogs and Service Manuals.

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

REMARK COMPLIANCE:


MECANICO INSPECTOR




Serial Number




CAPMODEL 206 SERIES


Nose Gear Turning Stop


206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 3,000 HRSP206-0001 Thru P20600647

REPEAT 1,000 HRS Thereafter

PURPOSETo check for possible damage to the nose gear turning radius stop pin.

INSPECTION INSTRUCTIONS1. Inspect the nose gear turning radius stop pin on the lower trunnion for damage.

ACCESS/LOCATION DETECTABLE CRACK SIZENose Gear N/A


REPAIR/MODIFICATIONIf the stop pin shows any indication of being bent, replace Stop Pin. Lower Trunnion stop pin hole diameter is 0.2492, + 0.0010, or -0.0000 inch.

COMMENTSRemainder of nose gear assembly must be inspected for additional damage.

REMARK COMPLIANCE:


MECANICO INSPECTOR




CAPMODEL 206 SERIES


Nose Gear Turning StopFigure 3-8




Serial Number


CAPMODEL 206 SERIES



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

EFFECTIVITY206-0001 Thru 206-0275 INSPECTION COMPLIANCEU206-0276 Thru U20607020P206-0001 Thru P20600647 INITIAL 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, replacement is 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 special notes on additional parts required when installing steering collar.

COMMENTSRef: SE71-4

REMARK COMPLIANCE:


MECANICO INSPECTOR




CAPMODEL 206 SERIES


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




CAPMODEL 206 SERIES


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




Serial Number


CAPMODEL 206 SERIES




Engine Compartment Wiring and Equipment Installation

EFFECTIVITY INSPECTION COMPLIANCE206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 6,000 HRS or 5 YRSP206-0001 Thru P20600647


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


CAPMODEL 206 SERIES




Fuselage Fwd Doorpost At Lower Corner of Windshield


U206-0273 Thru U20607020 REPEAT 1,000 HRSThereafter

PURPOSETo check for cracks in the outer flanges of the two nested channels that form the forward doorpost at the lower corner of the windshield.

INSPECTION INSTRUCTIONS1. Inspect for cracks radiating aft from the lower aft corner of the windshield in the two nested channels that form the forward doorpost.


Remove upholstery below windshield to gain access. Doorpost Channels OuterFlange - 1.5 inch

INSPECTION PROCEDUREVisually inspect for cracks radiating aft from the lower aft corner of the windshield in the two nested channels that form the forward doorpost.

REPAIR/MODIFICATIONReplace parts if crack is longer than the dimension given, if not stop drill the crack. (Refer to Detectable Crack Size).

COMMENTSReport any cracks found to Cessna Aircraft Co.Reference SEB 93-4 and SK206-41

REMARK COMPLIANCE:


MECANICO INSPECTOR




CAPMODEL 206 SERIES





Serial Number



Fuselage Forward Doorpost at Lower Corner Of Windshield Figure 3-12

CAPMODEL 206 SERIES


TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 53-40-01Fuselage Wing Strut Attach Forging



REPEAT 3,000 HRSThereafter

PURPOSETo check for possible cracks radiating out of wing strut attach holes and rivet holes attaching end fittings to the strut tube. 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 and working fasteners.

REPAIR/MODIFICATIONReplace wing strut attach forging if crack(s) radiate out from the attach hole. Contact Cessna for repair of the remaining 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 shall be half of the hours listed above.

REMARK COMPLIANCE:


MECANICO INSPECTOR

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



CAPMODEL 206 SERIES





Serial Number


Fuselage Wing Strut Attach Forging Figure 3-13

CAPMODEL 206 SERIES




Fuselage Wing Attachments




PURPOSETo 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




CAPMODEL 206 SERIES


Fuselage Wing Attachments Figure 3-14




Serial Number


CAPMODEL 206 SERIES




Fuselage Vertical Fin Attachments


P206-0001 Thru P2060647U206-0276 Thru U20601905 INITIAL 12,000 HRS


PURPOSEStructural Testing.


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

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




CAPMODEL 206 SERIES


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


CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS


CAPMODEL 206 SERIES






CAPMODEL 206 SERIES




Model/Type Total Time:



CAPMODEL 206 SERIES


Serial Number



Main Landing Gear Support Fittings


206-0001 Thru U20607020P206-0001 Thru P20600647 INITIAL 3,000 HRS


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




CAPMODEL 206 SERIES


Main Landing Gear Support ForgingsFigure 3-18




Serial Number



CAPMODEL 206 SERIES



Horizontal Stabilizer Aft Attach Bracket



REPEAT 200 HRSThereafter

PURPOSECracking has been experienced in the radius areas and the attach points of the bracket flanges on several high time airplanes.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.


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


REPAIR/MODIFICATIONReplacement Per SE 84-17

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




CAPMODEL 206 SERIES


IMPROVED STEEL BRACKETS (P/N 1232624-1) ARE AVAILABLEFOR THE FOLLOWING SERIALS:P206-0420 Thru P20600647 (1968 Thru 1970)U206-0915 Thru U20606832 (1968 Thru 1984)

Horizontal Stabilizer Attach BracketFigure 3-19




Serial Number



CAPMODEL 206 SERIES



Vertical Tail Fin Fuselage Attachments


206-0001 Thru U206-01905INITIAL 12,000 HRSREPEAT 6,000 HRS

Thereafter


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 and Sta. 230/260 aft bulkhead fin spar attachment.


REPAIR/MODIFICATIONContact Cessna Aircraft Company and define extent of damage.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




CAPMODEL 206 SERIES





AFN FIN SPAR ATTACHMENT Vertical Tail Fin Fuselage Attachments

Figure 3-20 (Sheet 1 of 5)

CAPMODEL 206 SERIES



CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS : 55-30-01


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

CAPMODEL 206 SERIES


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




CAPMODEL 206 SERIES


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




CAPMODEL 206 SERIES


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





CAPMODEL 206 SERIES


Serial Number



1. 0721402-3 Angle - Front Spar Splice LH 2. 0721400-13 Channel - Front Spar Splice LH3. 0721400-17 Plate - Front Spar Splice LH 4. Strut Attach Hole

EFFECTIVITY INSPECTION COMPLIANCE206-0001 Thru 206-0275U206-0276 Thru U20601700 INITIAL 12,000 HRS *P206-0001 Thru P20600647 REPEAT 2,000 HRS *


INSPECTION INSTRUCTIONS1. Eddy Current Inspect the cross-section of the front spar splice angle the complete length.

(Refer to step (5) for Eddy Current equipment.2. Eddy Current Inspect the lower 1/3 cross-section of the front spar splice channel the complete length. (Refer to

step (5).3. Eddy Current Inspect the lower 1/3 front spar splice plate. (Refer to step (5) for Eddy Current equipment.4. Eddy Current Inspect strut attach hole. (Refer to step (5) for Eddy Current equipment.5. 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 - 0.12 Inch.Support wing and remove strut. 4 - 0.06 Inch.


REPAIR/MODIFICATIONRemove and replace.

COMMENTSReport any cracks to Cessna.* Should any history of low level overland survey and patrol exist then the initial inspection compliance is 6000 hrs. and at 1000 hour intervals thereafter.

REMARK COMPLIANCE:


MECANICO INSPECTOR

Temporary Revision Number 1 (July 15, 1998) (D5121-1-13) 57-10-02


CAPMODEL 206 SERIES



NOTE: REMOVE INSPECTIONPLATE FOR CLARITY

Wing Station 100 Splice Inspection AreaFigure 3-22




CAPMODEL 206 SERIES



Serial Number



1. 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

EFFECTIVITYU20601701 Thru U20604649 INSPECTION COMPLIANCE

INITIAL 15,000 HRS*REPEAT 3,000 HRS *


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.



COMMENTSReport 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.




CAPMODEL 206 SERIES


NOTE: WITH THE ADDITION OF ITEM (6) THE FIRST SIGNIFICANT TEST SPECIMEN CRACKS WERE LOCAL SKIN CRACKING(S) AND A CRACK IN ITEM (6) (CRACKS NOT SHOWN IN ITEMS 5 AND 6).


REMARK COMPLIANCE:


MECANICO INSPECTOR



CAPMODEL 206 SERIES




Serial Number



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


U20604645 Thru U20607020 INITIAL 15,000 HRS*

REPEAT 3,000 HRS *


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


COMMENTSReport 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.




CAPMODEL 206 SERIES


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).


REMARK COMPLIANCE:


MECANICO INSPECTOR

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




CAPMODEL 206 SERIES


Serial Number



Rear Wing Spar Web - Inboard.

EFFECTIVITY *

INSPECTION COMPLIANCE206-0001 Thru 206-0275 INITIAL 3,000 HRSU206-0276 Thru U20601700P206-0001 Thru P20600647 REPEAT 1,000 HRS

Thereafter

PURPOSESome web cracking has been experienced subsequent to continued rough field usage.


1. Inspect web under wing rear spar fuselage attach fitting paying particular attention to web inboard edge shown on the following page.

2. Ensure that SEB85-9 has been complied with.

ACCESS/LOCATION DETECTABLE CRACK SIZERemove wing-to-fuselage fairing strip. Lower flaps and remove access cover. 0.06 Inch.Location: Web - Wing rear spar fuselage attach fitting area.


Visual

REPAIR/MODIFICATION

Rear Spar Kits Available - Refer to Service Bulletin SEB 85-9 Listed in Section I.

COMMENTS

* Refer to SEB85-9 for possible additional serials.Report any evidence of cracking to Cessna Aircraft Company.




CAPMODEL 206 SERIES


Rear Wing Spar Web-inboardFigura-3-25

REMARK COMPLIANCE:


MECANICO INSPECTOR




Serial Number


CAPMODEL 206 SERIES




Wing Fuselage Attach Fittings




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.




CAPMODEL 206 SERIES


Wing Fuselage Attach FittingsFigure 3-26

REMARK COMPLIANCE:


MECANICO INSPECTOR




Serial Number


CAPMODEL 206 SERIES



TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 57-10-07Wing Strut

EFFECTIVITY

INSPECTION COMPLIANCE206-0001 Thru U20601700

INITIAL 12,000 HRS *REPEAT 2,000 HRS *

PURPOSE

To check for cracks in wing strut and end fittings.


1. Visually inspect strut tube for cracks.2. Eddy Current Inspect for cracks radiating from the wing and fuselage attach holes in the wing strut end fittings.3. Eddy Current inspect per instructions in Section 4-0, Basic Information, pages x and xi.

ACCESS/LOCATION DETECTABLE CRACK SIZELoosen strut cuff fairing attachments.Support wing and remove strut. 0.080

INSPECTION PROCEDUREEddy Current and Visual

REPAIR/MODIFICATIONReplace wing strut.

COMMENTSReport wing strut cracks to Cessna Aircraft Company.* Should any history of low level overland survey or patrol exist, then the initial inspection compliance is 6,000 hours with repeat at 1,000 hour intervals thereafter.

REMARK COMPLIANCE:


MECANICO INSPECTOR




CAPMODEL 206 SERIES


Wing Strut InspectionsFigure 3-27




Serial Number


CAPMODEL 206 SERIES



TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 57-10-11Wing Strut Tube


206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 1,000 HRS*P206-0001 Thru P20600647

REPEAT 1,000 HRS *

PURPOSETo check strut tube for chafing cause by the door stop and/or strut cuff fairing.

INSPECTION INSTRUCTIONS1. Visually inspect wing strut tube for chafing or any other damage.2. Visually inspect wing strut tube for grooves caused by failed door stop and/or strut cuff fairing.

This criteria is as follows:(a) All strut braced 200 Series Airplanes Except 205, 206, 207, and 210. If the groove exceeds 0.010 inch in

depth and is less than 0.75 inch from a rivet center, the wing strut tube should be replaced.(b) Models 205, 206, 207, and 210 Airplanes. If the groove exceeds 0.020 inch in depth and is less than 0.75

inch from a rivet center, the wing strut tube should be replaced.(c) If the groove depth is less than that specified in the above steps, the wing strut may be repaired. Dye

Penetrant to ensure that crack(s) have not developed.

ACCESS/LOCATION DETECTABLE CRACK SIZELoosen strut cuff fairing attachments.Support wing and remove strut. 0.125


REPAIR/MODIFICATION1. Replace wing strut tube if required.2. Repair by tapering gradually to original surface and burnish to a smooth finish.

COMMENTSReport wing strut cracks to Cessna Aircraft Co.

REMARK COMPLIANCE:


MECANICO INSPECTOR




Serial Number


CAPMODEL 206 SERIES




Aileron Hinge Bracket

EFFECTIVITYP206-0001 Thru P20600647 INSPECTION COMPLIANCE206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 2,500 HRS


PURPOSE

Several reports on cracking of the lower forward tab flange and cracking out of the lower forward cutout aft of the tab (Ref. SE65-83).

INSPECTION INSTRUCTIONS1. Inspect flange area of bearing for cracks also.

ACCESS/LOCATION DETECTABLE CRACK SIZEEach aileron hinge bracket. 0.012 Inch.


REPAIR/MODIFICATIONRefer to SE65-83.Comply with AC 43-13-1 or replace.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR




CAPMODEL 206 SERIES


Aileron Hinge BracketFigure 3-32



CAPMODEL 206 SERIES




cap 206 series

Documents

indice general lista

pgina en blanco10

control y lista

experiencia en

contenidopagina section

aeronavegabilidad continuada18

aplicabilidad6 lista

fuselage wing attachments50