cap 206 series
TRANSCRIPT
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
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
PROGRAMADE AERONAVEGABILIDAD CONTINUADA
CAP
MANUAL Nº
REVISION Nº
ASIGNADO A:
FECHA: 08-ABRIL-2010 REVISIÓN: ORIGINAL PAGINA: 2
ORIGINAL
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
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
Página 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 REVISIÓN 15
B.5 REGISTRO DE REVISIONES 16
Página 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) 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....)
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LISTA DE CONTENIDO PAGINA
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
Página en blanco 28
SECTION II - LISTING OF CONTINUED AIRWORTHINESS PROGRAM INSPECTIONS 29- 30
INDICE GENERAL (Cont....)
LISTA DE CONTENIDO PAGINA
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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
Página en blanco 84
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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
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LISTA DE PÁGINAS EFECTIVAS
PAGINA REVISION FECHA
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LISTA DE PÁGINAS EFECTIVAS (Cont…)
PAGINA REVISION FECHA
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LISTA DE PÁGINAS EFECTIVAS (Cont…)
PAGINA REVISION FECHA
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PAGINA INTENCIONALMENTEDEJADO EN BLANCO
A.0 PROGRAMA DE AERONAVEGABILIDAD CONTINUADA (CAP)
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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
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Este organigrama obedece únicamente a los responsables directos de velar el cumplimiento del Programa de Aeronavegabilidad Continua (CAP).
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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
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
PAGINA INTENCIONALMENTEDEJADO EN BLANCO
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
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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.
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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
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PAGINA INTENCIONALMENTEDEJADO EN BLANCO
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.
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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.
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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.
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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.
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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.
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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
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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
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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.
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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:_________
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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
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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
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PAGINA INTENCIONALMENTEDEJADO EN BLANCO
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
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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
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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)
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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
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Trim Tab Actuator Mounting Bracket (R.H. Stabilizer)Figure 3-1
Revision 1: November 1993 (D5121-1-13) 27-30-01
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
Registration Fecha Apertura:
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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
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
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 27-30-02
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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
Revision 1: November 1993 (D5121-1-13) 27-30-02
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
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Registration Fecha Apertura:
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
INSPECTION PROCEDUREVisual
REPAIR/MODIFICATIONReplace as required.
COMMENTS
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 28-20-02
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 28-20-02
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Hose - Fuel VentFigure 3-3
Revision 1: November 1993 (D5121-1-13) 28-20-02
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
Registration Fecha Apertura:
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TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 28-30-01
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
INSPECTION PROCEDUREVisual
REPAIR/MODIFICATIONReplace as required.
COMMENTSRef: SE84-8
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 28-30-01
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 28-30-01
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 37
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Quick Drain Valves - Fuel Reservoir and Fuel TanksFigure 3-5
Revision 1: November 1993 (D5121-1-13) 28-30-01
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
Registration Fecha Apertura:
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TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 28-40-01Fuel Gaging Systems
EFFECTIVITY INSPECTION COMPLIANCE
206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 1,000 HRS or 3 YRSP206-0001 Thru P20600647
REPEAT 1,000 HRS or 3 YRS Thereafter
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
INSPECTION PROCEDUREVisual
REPAIR/MODIFICATIONAdjust/replace transmitter and/or gage as required.
COMMENTS
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 28-40-01
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
Registration Fecha Apertura:
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TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 29-10-01
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.
INSPECTION INSTRUCTIONS
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.
Revision 1: November 1993 (D5121-1-13) 29-10-01
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 29-10-01
NOTE
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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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 29-10-01
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 32-50-01
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 41
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Nose Gear Turning Stop
EFFECTIVITYINSPECTION COMPLIANCE
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
INSPECTION PROCEDUREVisual
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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 32-50-01
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 32-50-01
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 42
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Nose Gear Turning StopFigure 3-8
Revision 1: November 1993 (D5121-1-13) 32-50-01
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 43
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Registration Fecha Apertura:
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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 32-50-02
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 32-50-02
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 44
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Nose Gear Steering Collar & Upper Torque LinkFigure 3-9 (Sheet 1 of 2)
Revision 1: November 1993 (D5121-1-13) 32-50-02
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 32-50-02
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 45
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Nose Gear Steering Collar & Upper Torque LinkFigure 3-9 (Sheet 2 of 2)
Revision 1: November 1993 (D5121-1-13) 32-50-02
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 46
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 39-00-01
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
REPEAT 2,000 HRS or 2 YRS Thereafter
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
INSPECTION PROCEDUREVisual
REPAIR/MODIFICATION
COMMENTS
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 39-00-01
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 47
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 53-10-02
Fuselage Fwd Doorpost At Lower Corner of Windshield
EFFECTIVITY INSPECTION COMPLIANCE
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.
ACCESS/LOCATION DETECTABLE CRACK SIZE
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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 53-10-02
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 53-10-02
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 48
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Revision 1: November 1993 (D5121-1-13) 53-10-02
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
Registration Fecha Apertura:
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 49
Fuselage Forward Doorpost at Lower Corner Of Windshield Figure 3-12
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 53-40-01Fuselage Wing Strut Attach Forging
EFFECTIVITY INSPECTION COMPLIANCE
206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 12,000 HRSP206-0001 Thru P20600647
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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Temporary Revision Number 1 (D5121-1-13) 53-40-01 July 15, 1998
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 53-40-01
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 50
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Revision 1: November 1993 (D5121-1-13) 53-40-01
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 51
Fuselage Wing Strut Attach Forging Figure 3-13
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 53-40-02
Fuselage Wing Attachments
EFFECTIVITYINSPECTION COMPLIANCE
206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 12,000 HRSP206-0001 Thru P20600647
REPEAT 2,000 HRSThereafter
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.
ACCESS/LOCATION DETECTABLE CRACK SIZE
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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Temporary Revision Number 1 (D5121-1-13) 53-40-02 July 15, 1998
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 53-40-02
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 52
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Fuselage Wing Attachments Figure 3-14
Revision 1: November 1993 (D5121-1-13) 53-40-02
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 53
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 53-40-04
Fuselage Vertical Fin Attachments
EFFECTIVITYINSPECTION COMPLIANCE
P206-0001 Thru P2060647U206-0276 Thru U20601905 INITIAL 12,000 HRS
REPEAT 2,000 HRSThereafter
PURPOSEStructural Testing.
INSPECTION INSTRUCTIONS
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.
ACCESS/LOCATION DETECTABLE CRACK SIZE
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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 53-40-04
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 53-40-04
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 54
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Fuselage Vertical Fin AttachmentsFigure 3-16 (Sheet 1 of 4)
Revision 1: November 1993 (D5121-1-13) 53-40-04
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 55
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Revision 1: November 1993 (D5121-1-13) 53-40-04
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 53-40-04
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 56
Fuselage Vertical Fin AttachmentsFigure 3-16 (Sheet 2 of 4)
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Revision 1: November 1993 (D5121-1-13) 53-40-04
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 53-40-04
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 57
Fuselage Vertical Fin AttachmentsFigure 3-16 (Sheet 3 of 4)
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Revision 1: November 1993 (D5121-1-13) 53-40-04
Aircraft CESSNA LUGAR:
Model/Type Total Time:
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 58
Fuselage Vertical Fin AttachmentsFigure 3-16 (Sheet 4 of 4)
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Serial Number
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 53-40-06
Main Landing Gear Support Fittings
EFFECTIVITYINSPECTION COMPLIANCE
206-0001 Thru U20607020P206-0001 Thru P20600647 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.
INSPECTION PROCEDURE
Visual
REPAIR/MODIFICATION
Replace
COMMENTS
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 53-40-06
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 53-40-06
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 59
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Main Landing Gear Support ForgingsFigure 3-18
Revision 1: November 1993 (D5121-1-13) 53-40-06
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
Registration Fecha Apertura:
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 60
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 55-10-01
Horizontal Stabilizer Aft Attach Bracket
EFFECTIVITYINSPECTION COMPLIANCE
206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 1,000 HRSP206-0001 Thru P20600647
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.
INSPECTION INSTRUCTIONS
Visually inspect the stabilizer aft spar attach bracket per SE84-17.
ACCESS/LOCATION DETECTABLE CRACK SIZE
Remove horizontal stabilizer-to-fuselage fairings and stinger. N/A
INSPECTION PROCEDUREVisual
REPAIR/MODIFICATIONReplacement Per SE 84-17
COMMENTS
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 55-10-01
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 55-10-01
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 61
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
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
Revision 1: November 1993 (D5121-1-13) 55-10-01
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
Registration Fecha Apertura:
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 62
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 55-30-01
Vertical Tail Fin Fuselage Attachments
EFFECTIVITYINSPECTION COMPLIANCE
206-0001 Thru U206-01905INITIAL 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.
ACCESS/LOCATION DETECTABLE CRACK SIZE
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.
INSPECTION PROCEDUREVisual and Dye Penetrant
REPAIR/MODIFICATIONContact Cessna Aircraft Company and define extent of damage.
COMMENTS
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 55-30-01
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 55-30-01
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 63
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Revision 1: November 1993 (D5121-1-13) 55-30-01
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 55-30-01
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 64
AFN FIN SPAR ATTACHMENT Vertical Tail Fin Fuselage Attachments
Figure 3-20 (Sheet 1 of 5)
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Revision 1: November 1993 (D5121-1-13) 55-30-01
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS : 55-30-01
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 65
Vertical Tail Fin Fuselage Attachments Figure 3-20 (Sheet 2 of 5)
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Vertical Tail Fin Fuselage AttachFigure 3-20 (Sheet 3 of 5)
Revision 1: November 1993 (D5121-1-13) 55-30-01
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 55-30-01
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 66
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Vertical Tail Fin Fuselage AttachmentsFigure 3-20 (Sheet 4 of 5)
Revision 1: November 1993 (D5121-1-13) 55-30-01
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 55-30-01
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 67
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Vertical Tail Fin Fuselage AttachmentsFigure 3-20 (Sheet 5 of 5)
Revision 1: November 1993 (D5121-1-13) 55-30-01
Aircraft CESSNA LUGAR:
Model/Type Total Time:
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 68
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Serial Number
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 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
EFFECTIVITY INSPECTION COMPLIANCE206-0001 Thru 206-0275U206-0276 Thru U20601700 INITIAL 12,000 HRS *P206-0001 Thru P20600647 REPEAT 2,000 HRS *
PURPOSEStructural Testing.
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.
ACCESS/LOCATION DETECTABLE CRACK SIZE
W.S. 100 inspection plates - inspect both wings. 1, 2 & 3 - 0.12 Inch.Support wing and remove strut. 4 - 0.06 Inch.
INSPECTION PROCEDUREEddy Current
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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Temporary Revision Number 1 (July 15, 1998) (D5121-1-13) 57-10-02
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 69
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 57-10-02
NOTE: REMOVE INSPECTIONPLATE FOR CLARITY
Wing Station 100 Splice Inspection AreaFigure 3-22
Revision 1: November 1993 (D5121-1-13) 57-10-02
Aircraft CESSNA LUGAR:
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 70
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Model/TypeTotal Time:
Serial Number
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 57-10-03
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 *
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.
INSPECTION PROCEDUREEddy Current
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 8000 hrs. and at 1500 hour intervals thereafter.
Temporary Revision Number 1 (D5121-1-13) 57-10-03 July 15, 1998
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 57-10-03
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 71
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
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).
Wing Station 100 Splice Inspection AreaFigure 3-23
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 57-10-03
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 72
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 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
EFFECTIVITY INSPECTION COMPLIANCE
U20604645 Thru U20607020 INITIAL 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 SIZE
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.
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.
Temporary Revision Number 1 (D5121-1-13) 57-10-04 July 15, 1998
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 57-10-04
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 73
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1 : November 1993 (D5121-1-13) 57-10-04
Aircraft CESSNA LUGAR:
Model/Type Total Time:
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 74
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Serial Number
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 57-10-05
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.
INSPECTION INSTRUCTIONS
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.
INSPECTION PROCEDURE
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.
Revision 1: November 1993 (D5121-1-13) 57-10-05
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 57-10-05
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 75
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Rear Wing Spar Web-inboardFigura-3-25
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 57-10-05
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 76
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 57-10-06
Wing Fuselage Attach Fittings
EFFECTIVITYINSPECTION COMPLIANCE
206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 12,000 HRSP206-0001 Thru P20600647
REPEAT 3,000 HRSThereafter
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
INSPECTION PROCEDUREEddy Current
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.
Temporary Revision Number 1 (D5121-1-13) 57-10-06 July 15, 1998
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 57-10-06
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 77
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Wing Fuselage Attach FittingsFigure 3-26
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 57-10-06
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 78
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Registration Fecha Apertura:
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.
INSPECTION INSTRUCTIONS
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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Temporary Revision Number 1 (D5121-1-13) 57-10-07 July 15, 1998
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 57-10-07
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 79
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Wing Strut InspectionsFigure 3-27
Revision 1: November 1993 (D5121-1-13) 57-10-07
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 80
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 57-10-11Wing Strut Tube
EFFECTIVITY INSPECTION COMPLIANCE
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
INSPECTION PROCEDUREVisual and Dye Penetrant
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:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 57-10-11
Aircraft CESSNA LUGAR:
Model/TypeTotal Time:
Serial Number
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 81
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Registration Fecha Apertura:
TITLE CONTINUED AIRWORTHINESS INSPECTION NUMBER: 57-50-02
Aileron Hinge Bracket
EFFECTIVITYP206-0001 Thru P20600647 INSPECTION COMPLIANCE206-0001 Thru 206-0275U206-0276 Thru U20607020 INITIAL 2,500 HRS
REPEAT 2,500 HRSThereafter
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.
INSPECTION PROCEDUREVisual and Dye Penetrant
REPAIR/MODIFICATIONRefer to SE65-83.Comply with AC 43-13-1 or replace.
COMMENTS
REMARK COMPLIANCE:
FECHA DE CUMPLIMIENTO ……………………………………………………………..
MECANICO INSPECTOR
Revision 1: November 1993 (D5121-1-13) 57-50-02
CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 57-50-02
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 82
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
Aileron Hinge BracketFigure 3-32
Revision 1: November 1993 (D5121-1-13) 57-50-02
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 83
CAPMODEL 206 SERIES
SUPLEMENTO DEL PMA CONTINUED AIRWORTHINESS PROGRAM
PAGINA INTENCIONALMENTEDEJADO EN BLANCO
FECHA: 08-ABRIL-2010 REVISION: ORIGINAL PAGINA: 84