CAP 337 Series

CAPMODEL 337 SERIES

CONTINUED AIRWORTINESS PROGRAM

MODEL 300 SERIES PISTON

SINGLE ENGINE AIRCRAFT

PROGRAMADE AERONAVEGABILIDAD CONTINUADA

CAP

CARATULA

AUTOR: MELQUIADES CHAVEZ GALDOS

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

CAPMODEL 337 SERIES


PROGRAMADE AERONAVEGABILIDAD CONTINUADA

CAP

MANUAL Nº

REVISION Nº

ASIGNADO A:

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

ORIGINAL

CAPMODEL 337 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

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B. BOLETINES DE SERVICIO, NEWSLETTERS Y SERVICEKITS 19

C. ANALISIS 19

D. PRUEBAS 20

C. INSPECCION DEL AVION 20

3.0 REPORTE Y COMUNICACIONES 20

3.1 REPORTANDO LAS DISCREPANCIAS 21

3.2 DISPOSICION DEL FORMATO DE DISCREPANCIAS 21

3.3 ACCIONES DE SEGUIMIENTO DEL FABRICANTE 21

4.0 INFORMACION BASICA 22

4.1 INSPECCION 22

1. GENERAL 22

2. MATERIALS AND EQUIPEMENT 21

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....)



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SECTION III – CONTINUING AIRWORTHINESS PROGRAM INSPECTION 31

21-40-00 Heater Fuel Pump Shroud Drain Line and Vent Lines 31

25-10-00 Pilot and Copilot Seat Back Attachment 32

25-10-01 Pilot / Copilot Shoulder Harness Reel and Support 33

25-10-02 Seat Belt and Shoulder Harness Attachments 34

27-10-03 Aileron Trim Actuator Structure 35

27-10-04 Aileron Hinges and fittings 36

27-20-02 Rudder Control Surface Stop 37

27-20-03 Rudder Structure 38-39

27-20-04 Rudder Torque Tube 40-41

27-30-02 Elevator Arm Assembly and Pushrod 42

27-30-04 Elevator Trim Pulley Bracket Actuator Structure 43

35-10-00 Oxygen System Supply Lines 44

35-10-01 Oxygen System Supply Lines (cabin Section) 45

39-00-00 Wiring Installation - Wing 46

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

52-10-00 Cabin Door Retention 48

52-20-00 Emergency Exit Door lever Mechanism Inspection 49

53-10-00 Complete pressurized Cabin Structure Inspection 50

53-10-02 Fuselage rear Spar Attach Fitting Inspection 51-52

55-10-00 Horizontal Stabilizer Inspection 53

55-10-01 Horizontal Stabilizer Spars and Attachments 54

55-30-00 Vertical Stabilizer Spars and Attachments 55

55-30-01 Rudder hinges and fittings 56

57-10-00 Wing Strut and End Fitting 57 - 58

57-10-01 Wing Fuselage Attach Fittings 59 - 60

57-10-02 Wing Rear Spar Web 61 - 62

57-20-00 Wing Front Spar Inspection 63

79-10-00 Oil Filter Adapter 64



CAPMODEL 337 SERIES


APLICABILIDAD

MODEL SERIAL

337 Thru T337H-SP 337-0002 Thru 33701955

T337G Thru P337H P3370001 Thru 33700356

F337E/FT337E F3370001 Thru F33700055

F337EGP/FT337PH F33700001 Thru F33700023

OB-1402 AÑO DE FABRICACION 1975 SERIAL NUMBER P3370207

OB-1551 AÑO DE FABRICACION 1973 SERIAL NUMBER 33701544


CAPMODEL 337 SERIES


LISTA DE PÁGINAS EFECTIVAS

PAGINA REVISION FECHA

1 ORIGINAL 08-ABR-2010






























CAPMODEL 337 SERIES


LISTA DE PÁGINAS EFECTIVAS (Cont…)
































CAPMODEL 337 SERIES


LISTA DE PÁGINAS EFECTIVAS (Cont…)









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

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PAGINA INTENCIONALMENTEDEJADO EN BLANCO


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A.0 PROGRAMA DE AERONAVEGABILIDAD CONTINUADA (CAP)

A.1 INTRODUCCIÓN

El presente Programa de Aeronavegabilidad Continuada ha sido desarrollado por TRAVEL AIR E.I.R.L. en base al Manual D5307-1-13 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 brindar un servicio más eficiente con un alto grado de seguridad para nuestros clientes.


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A.4 ORGANIGRAMA

Este organigrama obedece únicamente a los responsables directos de velar el cumplimiento del Programa de Aeronavegabilidad Continuada (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 337 SERIES



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

B.1 CARATULA DEL PROGRAMA


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

B.2 CARATULA DE ASIGNACION DEL PROGRAMA

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 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.


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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.

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 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


CAPMODEL 337 SERIES


REVISIONFECHA DE REVISION

FECHA DE APROBACION

EFECTUADO POR

ORIGINAL 08-05-2010 CARLOS PALACIN CORCUERA


CAPMODEL 337 SERIES



CAPMODEL 337 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.

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


CAPMODEL 337 SERIES


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.

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’s) 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.


CAPMODEL 337 SERIES


La flota Cessna series 300 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.

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


CAPMODEL 337 SERIES


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 DISCREPANCIAS.

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.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


CAPMODEL 337 SERIES


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 300. Refiérase a los manuales de Servicio/Mantenimiento individuales de la serie 300 para los específicos programas de inspección de su aeronave.

NOTA.- Desde el párrafo 4.1 hasta la página final se mantendrán tal como fueron publicados en Ingles.

4.1. INSPECCION.

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.


CAPMODEL 337 SERIES


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

3. PROCEDURES

A. Surface Cleaning


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(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 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:


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Cessna 300 Series Service ManualCessna 300 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 300 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 300 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 300 series models. Service Bulletins considered mandatory for airworthiness will be listed in Section 1, TECHNICAL DOCUMENT REFERENCE.

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.


CAPMODEL 337 SERIES


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) 941-7550/Fax (316) 942-9006.

CESSNA AIRCRAFT COMPAINYMODEL 200 SERIES

CONTINUED AIRWORTHINESS PROGRAM

Discrepancy Report

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

AIRPLANE:_________

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

Component Total Hours____________ Cycles N/A

SERVICE HISTORY:

____________________________________________________________________________________

____________________________________________________________________________________

____________________________________________________________________________________


CAPMODEL 337 SERIES


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

Super Skymaster service Manual D2500-1-13 337 Super Skymaster (1965 -1973)

337 & Turbo Series service Manual D2506-8-13 337/T337 Skymaster (1974 -1980)

337 Pressurized Series D2516-9-13 P337 Pressurized Skymaster (1973 -1980)

To purchase Manuals, write to:Cessna Aircraft Company Dept. 751CP.O. Box 7706Wichita, Kansas 67277Telephone 1-316-517-5800FAX: 1-316-517-7271


CAPMODEL 337 SERIES


SERVICE BULLETINS

Number Title Date Cap Insp

SL63-50 Auxiliary Fuel Selector Valve Inspection 1 0/30/63 28-20-00SL65-18 Manifold Drain Lines Inspection 71 -70-00ME69-11 Exhaust System Joint Spring Inspection 5/1/69 78-1 0-01ME69-14 Fuel Line Support 6/12/69 28-10-01ME69-21 Induction Airbox Inspection 7/22/69 71-60-00M E70-4 Oil Filter Adapter Inspection 1/9/70 79-1 0-00ME70-7 Fuel Pump Filter Inspection 1/30/70 28-1 0-02ME70-14 Fuel Line Inspection 3/24/70 28-1 0-03ME70-29 Aileron Stop Bolt Inspection 7/31/70 27-1 0-02ME71-27 Nose Gear Steering Bolts Inspection 1/7/72 32-50-00ME72-11 Firewall Screw Inspection and Replacement 2/16/73 28-1 0-04ME72-26 Front Wing Spar Inspection 12/12/72 57-20-00ME73-4 Tip Tank Nose Caps - Fuel Seal Inspection 1 1/22/74 28-1 0-05ME74-4 Front Carry-Thru Spar Inspection 3/29/74 57-1 0-01ME75-23 Main Landing Fork Bolt Inspection 9/19/75 32-1 0-00ME78-7 Fuel Tank Inspection 3/13/78 28-1 0-00ME88-5 Nose Gear Trunnion Inspection 1/31/92 32-30-00MEB92-8 Seat Belt and Shoulder Harness Installation 9/4/92 25-1 0-01

Service Bulletins listed above, write to:Cessna Aircraft Company Supply DivisionDept 753C.P.O. Box 7706Wichita, Kansas 67277


CAPMODEL 337 SERIES



SECTION II - LISTING OF P337 SERIES CONTINUED AIRWORTHINESS PROGRAM INSPECTIONS

OB-1402 AÑO DE FABRICACION 1975 SERIAL NUMBER P3370207

ContinuedAirworthiness

Program Inspection

Inspection ComplianceNumber

TitleModel Effectivity INITIAL REPEAT

21-40-00Heater Fuel Pump Shroud Drain Line and Vent Lines

337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

1,000 Hrs

1,000 Hrs

25-10-00Pilot and Copilot Seat Back

Attachment337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

5,000 Hrs

2,500 Hrs

25-10-01Pilot / Copilot Shoulder

Harness Reel and Support337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

2 Yrs 2 Yrs


CAPMODEL 337 SERIES


25-10-02Seat Belt and Shoulder Harness Attachments


337-0002 Thru 337-01955P3370001 Thru P3370356

2 Yrs 2 Yrs

27-10-03Aileron Trim Actuator

Structure337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

1,000 Hrs

or 3 Yrs

1,000 Hrs

or 3 Yrs

27-10-04 Aileron Hinges and fittings337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

15,000Hrs

3,750Hrs

27-20-02Rudder Control Surface

Stop337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

7500 Hrs 2500 Hrs

27-20-03 Rudder Structure337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

7500 Hrs 2500 Hrs

27-20-04 Rudder Torque Tube337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

7500 HrsOr 3 Yrs

2500 HrsOr 3 Yrs

27-30-02Elevator Arm Assembly

and Pushrod337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

7500 Hrs 2500 Hrs

27-30-04Elevator Trim Pulley

Bracket Actuator Structure337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

7500 Hrs 2500 Hrs

35-10-00Oxygen System Supply

Lines337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

10,000Hrs

5,000Hrs

35-10-01Oxygen System Supply

Lines(Cabin Section)


337-0002 Thru 337-01955P3370001 Thru P3370356

10,000Hrs

5,000Hrs

39-00-00 Wiring Installation - Wing337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

1,000Hrs

or 2 Yrs

1,000Hrs

or 2 Yrs

39-00-01Engine compartment

Wiring and Equipement Installation


337-0002 Thru 337-01955P3370001 Thru P3370356

5,000Hrs

or 5 Yrs

2,000Hrs

or 2 Yrs

52-10-00 Cabin Door Retention337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

10,000Hrs

5,000Hrs

52-20-00Emergency Exit Door lever

Mechanism Inspection337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

1,000Hrs

1,000Hrs

LISTING OF CONTINUED AIRWORTHINESS PROGRAM INSPECTIONS (Cont…)

ContinuedAirworthiness

Program Inspection

Inspection ComplianceNumber

TitleModel Effectivity INITIAL REPEAT

53-10-00Complete pressurized

Cabin Structure InspectionT337G Thru P337H P3370001 Thru P3370356

10,000Hrs

5,000Hrs

53-10-02Fuselage rear Spar Attach

Fitting Inspection337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

12,000Hrs

3,000Hrs

55-10-00Horizontal Stabilizer

Inspection337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

10,000Hrs

5,000Hrs


CAPMODEL 337 SERIES


55-10-01Horizontal Stabilizer Spars

and Attachments337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

15,000Hrs

5,000Hrs

55-30-00Vertical Stabilizer Spars and Attachments


337-0002 Thru 337-01955P3370001 Thru P3370356

15,000 Hrs

5,000 Hrs

55-30-01 Rudder hinges and Fittings337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

15,000 Hrs

3,750 Hrs

57-10-00 Wing Strut and End Fitting 337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

12,000Hrs

2,000Hrs

57-10-01Wing Fuselage Attach Fittings


337-0002 Thru 337-01955P3370001 Thru P3370356

12,000 Hrs

3,000 Hrs

57-10-02 Wing Rear Spar Web337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

12,000 Hrs

3,000 Hrs

57-20-00 Wing Front Spar Inspection337 Thru T337H-SPT337G Thru P337H

337-0002 Thru 337-01955P3370001 Thru P3370356

10,000 Hrs

5,000 Hrs

79-10-00 Oil Filter Adapter337 Thru T337H-SP 337-0002 Thru 337-01955

1,000 Hrs

or 1 Yrs

1,000Hrs

Or 1 Yrs

SECTION III - CONTINUING AIRWORTHINESS PROGRAM INSPECTION

Aircraft CESSNA LUGAR:

Model/TypeTotal Time:

Serial Number

Registration Fecha Apertura:

TITLE Heater Fuel Pump Shroud Drain Line and Vent Lines: 21-40-00

MODEL EFFECTIVITYINSPECTION

COMPLIANCE

337 Thru T337H-SP 337-0002 Thru 33701955 INITIAL 1,000 HRS T337G Thru P337H P3370001 Thru P3370356 REPEAT 1,000 HRS

ThereafterPURPOSEVerify integrity of fuel pump shroud overboard drain line, heater vent lines and fuel pump shroud.


CAPMODEL 337 SERIES

CONTINUED AIRWORTINESS PROGRAMINSPECTION INSTRUCTIONS1. Inspect fuel pump shroud drain line for joint tightness and security. 2. Check for protrusion of line thru nose skin and ensure that scarf angle is facing aft.3. Inspect fuel pump shroud and heater fuel inlet shroud for tightness of joints and security.4. Inspect all fuel and vent lines for corrosion, tightness of joints and security

ACCESS/LOCATION DETECTABLE CRACK SIZERight Nose section N/A

INSPECTION PROCEDUREVisual

REPAIR/MODIFICATIONTighten fuel lines and position scarf in the proper direction as required

COMMENTSA fuel pump rupture will permit fuel to flow thru the shroud drain line. If the line is not vented overboard fuel will leak inside nose baggage area.

REMARK COMPLIANCE:

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

MECANICO INSPECTOR

(D5307-1-13) 21-40-00



Serial Number


TITLE Pilot And Copilot Seat Back Attachment: 25-10-00


COMPLIANCE

337 Thru T337H-SP 337-0002 Thru 33701955 INITIAL 5,000 HRS T337G Thru P337H P3370001 Thru P3370356 REPEAT 2,500 HRS

Thereafter

PURPOSETo verify integrity of pilot and copilot seat back to seat base attachment.

INSPECTION INSTRUCTIONS


CAPMODEL 337 SERIES

CONTINUED AIRWORTINESS PROGRAM1. Inspect seat back to seat base pivot pins, seat base pivot bracket, and back attachment to pivot structure for the

following: Looseness, permanent set, excessive wear, corrosion and missing or broken fasteners.

ACCESS/LOCATION DETECTABLE CRACK SIZECabin N/A


REPAIR/MODIFICATIONRepairs may be made in accordance with applicable Cessna Service Manual and/or MEB89-3, Revision 1. Any repair not covered by recommendations in the above document should be coordinated with Cessna Technical information Service prior to beginning repair.

COMMENTSPilot or copilot seat back failure could result in the operator losing control of the airplane under certain conditions.

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 25-10-00



Serial Number


TITLE Pilot/ Copilot Shoulder Harness Reel and Support: 25-10-01


COMPLIANCE

337 Thru T337H-SP 337-0002 Thru 33701955 INITIAL 2 Yrs T337G Thru P337H P3370001 Thru P3370356 REPEAT 2 Yrs

Thereafter

PURPOSETo ensure shoulder harness reels function properly and their attachment is secure.


CAPMODEL 337 SERIES

CONTINUED AIRWORTINESS PROGRAMINSPECTION INSTRUCTIONS1. Remove inertia reel in accordance with the applicable Service Manual2. Inspect inertia reel to ensure proper function and secure attachment to under structure.3. Inspect under structure for cracks and corrosion.4. Reinstall inertia reel in accordance with the applicable Service Manual.

ACCESS/LOCATION DETECTABLE CRACK SIZE

Under Royalite cover N/A

INSPECTION PROCEDURE

Refer to inspection instructions above

REPAIR/MODIFICATION

Repair or replace as required in accordance with the applicable Service Manual.

COMMENTS

Ref: MEB92-8

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 25-10-01



Serial Number


TITLE Seat Belt and Shoulder Harness Attachments: 25-10-02


COMPLIANCE

337 Thru T337H-SP 337-0002 Thru 33701955 INITIAL 2 Yrs T337G Thru P337H P3370001 Thru P3370356 REPEAT 2 Yrs

Thereafter

PURPOSEEnsure seat belts and attaching structure are secure and have not deteriorated.


CAPMODEL 337 SERIES

CONTINUED AIRWORTINESS PROGRAMINSPECTION INSTRUCTIONS

1. Remove seat in accordance with Service Manual2. Inspect all seat belts, attachments and under structure for cracks, corrosion and security.


Fuselage N/A


Visual

REPAIR/MODIFICATION

Repair or replace as required.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 25-10-02



Serial Number


TITLE Aileron Trim Actuator Structure: 27-10-03


COMPLIANCE

337 Thru T337H-SP 337-0002 Thru 33701955 INITIAL 1,000 Hrs or 3 Yrs T337G Thru P337H P3370001 Thru P3370356 REPEAT 1,000 Hrs or 3 Yrs

Thereafter

PURPOSEVerify integrity of aileron trim actuator clamps attachment.



CAPMODEL 337 SERIES


1. Remove aileron trim actuator in accordance with the applicable Service Manual 2. Inspect all fasteners and attaching structure for integrity.3. Inspect actuator mounting structure for corrosion, bent or deformed flanges, cracks, and fasteners integrity4. Install aileron trim actuator in accordance with applicable Service Manual


Wing N/A


Visual

REPAIR/MODIFICATION

Repairs may be made in accordance with applicable Cessna Service Manual. Any repair not covered by recommendations in above documents should be coordinated with Cessna Technical information Service prior to beginning repair.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 27-10-03



Serial Number


TITLE Aileron Hinges and Fittings: 27-10-04


COMPLIANCE

337 Thru T337H-SP 337-0002 Thru 33701955 INITIAL 15,000 Hrs T337G Thru P337H P3370001 Thru P3370356 REPEAT 3,750 Hrs

Thereafter

PURPOSETo inspect aileron hinges, fittings and associated hardware and components for condition.



CAPMODEL 337 SERIES


1. Remove ailerons in accordance with applicable Service Manual 2. Visually inspect aileron hinges for condition, cracks, and security; hinge bolts, hinge bearings for condition and

security; bearings for freedom of rotation; attach fittings for evidence of damage wear, failed fasteners and security.

3. Dye penetrant inspect aileron hinge attach fittings for cracks.4. Reinstall aileron in accordance with applicable Service Manual.


Left / Right Wing N/A


Visual/ Dye Penetrant

REPAIR/MODIFICATION

Replace worn/damaged components with latest superseding part numbers.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 27-10-04



Serial Number


TITLE Rudder Control Surface Stops: 27-20-02


COMPLIANCE


Thereafter

PURPOSE

Verify integrity of rudder stops


CAPMODEL 337 SERIES



1. Inspect stop bolts for worn threads, bending, and corrosion. 2. Adjust stops to setting defined in applicable Service Manual.


Vertical Stabilizer N/A


REPAIR/MODIFICATIONRepairs may be made in accordance with applicable Cessna Service Manual. Any repair not covered by recommendations in above documents should be coordinated with Cessna Technical Information Service prior to beginning repair.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 27-20-02



Serial Number


TITLE Rudder Structure: 27-20-03


COMPLIANCE


Thereafter

PURPOSE


CAPMODEL 337 SERIES


To ensure structural integrity of rudder assembly


1. Inspect rudder for deterioration resulting from fatigue, wear, overload, wind damage, and corrosion. 2. Inspect skins, spars, ribs, and hinge brackets for cracks, corrosion, and working fasteners.3. Remove bolt and inspect hinge bolt holes for elongation and wear.4. Install hinge bolt in accordance with applicable Service Manual.


Rudder N/A



COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS: 27-20-03


CAPMODEL 337 SERIES


(D5307-1-13) 27-20-03



Serial Number



Rudder Structure Figure 3 – 5

CAPMODEL 337 SERIES


TITLE Rudder Torque Tube: 27-20-04


COMPLIANCE

337 Thru T337H-SP 337-0002 Thru 33701955 INITIAL 7,500 Hrs or 10 YrsT337G Thru P337H P3370001 Thru P3370356 REPEAT 2,500 Hrs or 3 Yrs

Thereafter

PURPOSE

To ensure structural integrity of rudder torque tube assembly


1. Remove rudder torque tube access plates in accordance with applicable Service Manual. 2. Inspect weld on torque tube for cracks.3. Inspect torque tube for internal rusting.4. Install rudder torque tube access plates in accordance with applicable Service Manual.


Rudder N/A



COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 27-20-04



CAPMODEL 337 SERIES


(D5307-1-13) 27-20-04



Serial Number


Rudder Torque Tube Figure 3 – 6

CAPMODEL 337 SERIES



TITLE Elevator Arm Assembly and Pushrod: 27-30-02


COMPLIANCE


Thereafter

PURPOSE

To inspect elevator control components.


1. Remove elevator arm assembly and aft elevator pushrod from airplane in accordance with applicable Service Manual.

2. Examine arm assembly for evidence of corrosion loose rivets and cracks. Check bearing for looseness and freedom of movement.

3. Examine pushrod for evidence of corrosion, hole elongation, cracks, and clevis retention.


Tailcone N/A



COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13)

27-30-02



Serial Number


CAPMODEL 337 SERIES



TITLE Elevator Trim Pulley Bracket Actuator Structure: 27-30-04


COMPLIANCE


Thereafter

PURPOSEVerify the integrity of the pulley brackets and actuator support brackets.


1. Remove chain/cable assembly, actuator assembly, and pushrod assembly from airplane in accordance with applicable Service Manual.

2. Inspect pulley brackets for cracks, corrosion, and bent flanges.3. Inspect all pulleys for wear, flat spot, and freedom of rotation.4. Inspect all fasteners and attaching structure for integrity.5. Install chain/cable assembly, actuator assembly, and pushrod assembly in accordance with applicable Service

Manual


Elevator N/A



COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 27-30-04


Model/Type Total Time:


CAPMODEL 337 SERIES


Serial Number


TITLE Oxygen System Supply Lines: 35-10-00


COMPLIANCE


ThereafterPURPOSE

To verify the integrity of the oxygen system in the nose section.


1. Inspect oxygen lines for signs of corrosion, security of joints, and interference with structure or equipment.


Nose Section/ Tailcone N/A



COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13)

35-10-00




CAPMODEL 337 SERIES


Serial Number


TITLE Oxygen System Supply Lines (Cabin Section): 35-10-01


COMPLIANCE


ThereafterPURPOSE

To verify integrity of oxygen system in cabin section.


1. Remove headliner and upholstery as required in accordance with applicable Service Manual to gain access to oxygen lines.

2. Inspect oxygen lines for signs of corrosion, security of joints, and interference with structure or equipment.

3. Install headliner and upholstery as required in accordance with applicable Service Manual.


Headliner and side wall areas N/A



COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13)

35-10-01




CAPMODEL 337 SERIES


Serial Number


TITLE Wiring Installation - Wing: 39-00-00


COMPLIANCE

337 Thru T337H-SP 337-0002 Thru 33701955 INITIAL 1,000 Hrs or 2 Yrs.T337G Thru P337H P3370001 Thru P3370356 REPEAT 5,000 Hrs or 2 Yrs.

ThereafterPURPOSE

To inspect for possible deterioration after an extended period of time.


1. Remove all inspection plates, open all access doors along wing, and open up wing root area (both left and right wings).

2. Remove components as necessary to allow inspection of all wiring in both wings.3. Inspect condition of wiring and sleeving, wire supports, etc.4. Check for any wire abrasion against sheet metal surfaces and assure that all wiring is secured properly.5. Check electrical connectors for any sign of contact corrosion, security of contacts and of wiring at contacts


Wing N/A


REPAIR/MODIFICATIONReplace wiring as required.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 39-00-00



Serial Number


CAPMODEL 337 SERIES



TITLE Engine Compartment Wiring And Equipment Installation: 39-00-01


COMPLIANCE

337 Thru T337H-SP 337-0002 Thru 33701955 INITIAL 5,000 Hrs or 5 Yrs.T337G Thru P337H P3370001 Thru P3370356 REPEAT 2,000 Hrs or 2 Yrs.

Thereafter

PURPOSE

To inspect for possible deterioration after an extended period of time.


1. Remove components as necessary to allow inspection of the entirety of all wiring.2. Inspect all wiring, protective sleeving, clamps, supports, etc. for signs of deterioration due to heat, abrasion

vibration, etc.3. Ensure all wiring is properly supported and secured in such a manner that the wiring will not come in contact with

sharp edges of sheet metal parts, engine controls or engine components that operate at elevated temperatures.4. Inspect all electrical grounds at firewall for security and corrosion.5. Ensure terminals of sender units on engine are secure and wiring is free of damage from heat or abrasion.6. Ensure engine is properly grounded to airframe.


Engine compartment N/A


REPAIR/MODIFICATIONReplace wiring as required.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 39-00-01



Serial Number



CAPMODEL 337 SERIES


TITLE Cabin Door Retention: 52-10-00


COMPLIANCE


Thereafter

PURPOSE

Verify the integrity of the door retention system.


1. Remove all pin retention linkages from upper and lower cabin door in accordance with applicable Service Manual.

2. Inspect all bellcranks, pushrods, handles, and pins for cracks, corrosion, worn holes and signs of fatigue.3. Dye penetrant inspect latch pin receptacles for corner cracks.4. Install all pin retention linkages in accordance with applicable Service Manual.


Cabin Door N/A

INSPECTION PROCEDUREVisual and Dye Penetrant Inspection


COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

D5307-1-13) 52-10-00



Serial Number


CAPMODEL 337 SERIES



TITLE Emergency Exit Door Lever Mechanism Inspection: 52-20-00


COMPLIANCE


Thereafter

PURPOSE

To ensure emergency exit door lever mechanism has not deteriorated and is functioning properly.


1. Remove Royalite panels and visually inspect lever for cracks, wear and damage.

2. Visually inspect other lever mechanism parts and components for cracks, wear, damage and deterioration.

3. Check operation of lever mechanism.


Emergency Exit Door N/A


REPAIR/MODIFICATION

Replace any worn, cracked, damaged or deteriorated parts with new parts as required.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

D5307-1-13) 52-20-00




CAPMODEL 337 SERIES


Serial Number


TITLE Complete Pressurized Cabin Structure Inspection: 53-10-00MODEL EFFECTIVITY

INSPECTION COMPLIANCE

INITIAL 10,000 Hrs T337G Thru P337H P3370001 Thru P3370356 REPEAT 5,000 Hrs

Thereafter

PURPOSETo inspect specified areas of the pressurized cabin structure for indications of deterioration.


1. Visually Inspect cabin entry door and emergency exit door frames for corrosion, cracks, loose or missing fasteners and signs of deterioration.

2. Visually Inspect all window frames and surrounding structure for corrosion, cracks, loose or missing fasteners and signs of deterioration.

3. Visually Inspect forward and aft pressure bulkhead for corrosion, cracks, loose or missing fasteners and signs of deterioration.

4. Visually Inspect cabin frame structure below floorboards for corrosion, cracks, loose or missing fasteners and signs of deterioration.


Fuselage No



COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

D5307-1-13) 53-10-00




CAPMODEL 337 SERIES


Serial Number


TITLE Fuselage Rear Spar Attach Fittings Inspection: 53-10-02


COMPLIANCE


ThereafterPURPOSE

To ensure integrity fuselage rear spar attach fitting.


1. Inspect for possible cracking attachment hole. (Refer to step 4.)2. Possible galling or deformation os wing attachment holes. (Refer to step 4.)3. Do not remove wing attach bolts unless cracking or looseness is suspected. (Refer to step 4.)4. Eddy Current Inspect, per instructions in Section 4-0, “Basic Information”


Remove wing-to-fuselage fairing strips. No Cracks Allowed


Eddy Current

REPAIR/MODIFICATION

Replace fuselage rear spar attach fitting in accordance with applicable Service Manual.


CAPMODEL 337 SERIES



COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 53-10-02



Serial Number


Fuselage rear Spar Attach Fitting Inspection Figure 3 – 17 (Sheet 1)

CAPMODEL 337 SERIES



TITLE Horizontal Stabilizer Inspection: 55-10-00


COMPLIANCE


Thereafter

PURPOSE

To inspect for skin and rib cracks on upper and lower surface of horizontal stabilizer.


1. Inspect the upper and lower horizontal stabilizer skin area between front and rear spar at left/right horizontal stabilizer for cracks.


Tailcone N/A



COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

D5307-1-13) 55-10-00



Serial Number


CAPMODEL 337 SERIES



TITLE Horizontal Stabilizer Spars and Attachments: 55-10-01


COMPLIANCE


Thereafter

PURPOSE

Inspect horizontal stabilizer spars and attachments for signs of damage, fatigue and deterioration.


1. Remove elevator from airplane and open all horizontal stabilizer access panels in accordance with appropriate Service Manual.

2. Inspect forward and aft spars and attach fittings for cracks, corrosion, loose fasteners, elongated fastener attach holes and signs of fatigue and deterioration.


Tailcone N/A



COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

D5307-1-13) 55-10-01



Serial Number


CAPMODEL 337 SERIES



TITLE Vertical Stabilizer Spars and Attachments: 55-30-00


COMPLIANCE


Thereafter

PURPOSE

Inspect vertical stabilizer spars and attachments for signs of damage, fatigue and deterioration.


1. Remove rudder from airplane and open all vertical stabilizer access panels in accordance with appropriate Service/Maintenance Manual.

2. Inspect forward and aft spars and attach fittings for cracks, corrosion, loose fasteners, elongated fastener attach holes and signs of fatigue and deterioration.


Tailcone N/A


REPAIR/MODIFICATIONIf cracks or other damaged is found, contact Cessna Aircraft Company, and describe condition.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 55-30-00



Serial Number


CAPMODEL 337 SERIES



TITLE Rudder Hinges and Fittings: 55-30-01


COMPLIANCE


Thereafter

PURPOSE

To inspect rudder hinges, fittings, associated hardware and components for condition.


1. Remove rudder in accordance with applicable Service Manual.2. Visually inspect rudder hinges for condition, cracks and security; hinge bolts, hinge bearings for condition and

security; bearings for freedom of rotation; attach fittings for evidence of damage, wear, failed fasteners and security.

3. Dye penetrant inspect rudder hinge attach fittings for cracks4. Reinstall rudder in accordance with applicable Service Manual.

ACCESS/LOCATION DETECTABLE CRACK SIZEVertical Stabilizer

N/A

INSPECTION PROCEDUREVisual / Dye Penetrant

REPAIR/MODIFICATIONReplace defective/damaged components with the latest superseding part numbers.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR

D5307-1-13) 55-30-01



Serial Number



CAPMODEL 337 SERIES


TITLE Wing Strut and End Fitting: 57-10-00


COMPLIANCE

337 Thru T337H-SP 337-0002 Thru 33701955 INITIAL 12,000 Hrs *T337G Thru P337H P3370001 Thru P3370356 REPEAT 2,000 Hrs *

Thereafter

PURPOSETo check for cracks in wing strut and end fittings.

INSPECTION INSTRUCTIONS1. Visually Inspect strut assembly for cracks.2. Eddy Current Inspect, per instructions in Section 4-0, "Basic lnformation."


Loosen strut cuff fairing attachments. No Cracks Allowed

Support wing and remove strut.


Eddy Current and Visual

REPAIR/MODIFICATIONReplace wing strut in accordance with applicable Service Manual.

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 6000-hours with repeat at 1000-hour intervals thereafter.

REMARK COMPLIANCE:


MECANICO INSPECTOR



CAPMODEL 337 SERIES


(D5307-1-13) 57-10-00



Serial Number



Wing Strut Inspection Figure 3 -21

CAPMODEL 337 SERIES


TITLE Wing Fuselage Attach Fittings Inspection: 57-10-01


COMPLIANCE


ThereafterPURPOSE

To eddy current inspect primary load path of forward and aft spar fitting. There is one known history of cracking, except for rear spar web referred to in CAP Item 57-10-03.


1. 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. Check wing attach bolts for looseness, lf bolts are loose, remove wing attach bolts and inspect for cracks. (Refer

to step 4.)4. Eddy Current Inspect, per instructions in Section 4-0, "Basic Information."


Remove wing-to-fuselage fairing strips. No Cracks Allowed


Eddy Current

REPAIR/MODIFICATION

Replace wing cracked part

COMMENTS

Ref: ME74-4

Contac Cessna Aircraft Company for instructions if oversize holes are found.



CAPMODEL 337 SERIES


REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 57-10-01



Serial Number


TITLE Wing Rear Spar Web: 57-10-02


Wing FuselageAttach Fitting Figure 3 -22

CAPMODEL 337 SERIES



COMPLIANCE


Thereafter

PURPOSETo ensure integrity of the wing spar web.


1. Inspect web under wing rear spar fuselage attach fitting, paying particular attention to web inboard edge.


Remove wing-to-fuselage fairing strips. N/A

Lower flaps and remove access cover.

Location: Web – Wing rear spar fuselage attach fitting area.


Visual

REPAIR/MODIFICATIONReplace any evidence of cracking to Cessna Aircraft Company.

COMMENTS

REMARK COMPLIANCE:


MECANICO INSPECTOR



CAPMODEL 337 SERIES


(D5307-1-13) 57-10-02



Serial Number


TITLE Wing Front Spar Inspection: 57-20-00


Rear Wing Spar Web – Inboard Figure 3 -23

CAPMODEL 337 SERIES



COMPLIANCE


Thereafter

PURPOSETo check for cracks in front wing lower cap fittings.


1. Visually inspect strut tube for cracks.2. Eddy Current Inspect, per instructions in Section 4-0, "Basic Information."


Wing Root. No Crack Allowed


Eddy Current and Visual

REPAIR/MODIFICATIONReplace both wing in accordance with applicable Service Manual, if cracks were found.

COMMENTSRef: ME72-26 Front Wing Spar Inspection December 12,1972Ref: ME76-3 Front Wing Spar Inspection January 9, 1976Ref: ME78-2 Front and Rear Spar Inspection February 13, 1978* Should any history of low level overland survey or patrol exist, then the initial inspection compliance is 3000-hours with repeat at 300-hours intervals thereafter.

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 57-20-00



Serial Number



CAPMODEL 337 SERIES


TITLE Oil Filter Adapter Inspection: 79-10-00


COMPLIANCE

337 Thru 337G 337-0002 Thru 33701955 INITIAL 1,000 Hrs or 1 Yrs.REPEAT 1,000 Hrs or 1 Yrs.

ThereafterPURPOSETo visual inspect integrity of oil filter adapter.


1. Remove oil filter adapter from engine in accordance with applicable Service Manual.2. Visually inspect adapter for cracks.

ACCESS/LOCATION DETECTABLE CRACK Engine Nacelle

N/A


Visual

REPAIR/MODIFICATIONReplace oil filter adapter in accordance with applicable Service Manual.Install new oil filter in accordance with applicable Service Manual.

COMMENTSRef. ME70-4

REMARK COMPLIANCE:


MECANICO INSPECTOR

(D5307-1-13) 79-10-00


CAPMODEL 337 SERIES




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CAP 337 Series

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