# REVISION

MODEL LC40 -550 FG MAINTENA NCE MANUAL

REVISION 2 1 JULY 2012



# 300MM02

Please replace the current manual in its entirety.

# Maintenance Manual



# MODEL LC40-550FG

Member of GAMA

COPYRIGHT © 2009 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA 

# 1 FEBRUARY 2009

300MM02 

## REVISION 2 1 JULY 2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL



## LIST OF EFFECTIVE PAGES

CHAPTER-SECTION-SUBJECT PAGE DATE
00-Title 00-List of Effective Pages
00-Record of Revisions 00-Record of Temporary Revisions
00-Table of Contents LIST OF REVISIONS Page 1 Jul 1/2012
GENERAL DESCRIPTION OF THE LC40-550FG Pages 1-5 Feb 1/2009 INTRODUCTION Pages 1-6 Feb 1/2009



## 00 - LIST OF EFFECTIVE PAGES Page 1 of 1 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

LIST OF REVISIONS

1. Revisions A. This Maintenance Manual includes the original issue and the revisions listed in Table 1. Put revisions in this manual when they are received. This will make sure that this manual has the most current maintenance and inspection procedures.
Table 1. Original Issue - Mar 1/2009

Revision Number Date Revision Number Date
1 Jan 1/2012 2 Jul 1/2012

B. FAA Approved Airworthiness Limitations are incorporated in this maintenance manual as Chapter 4. Revisions to Chapter 4 are dated as approved by the FAA Regional Manager, Aircraft Certifi cation Of

fi ce. To make sure that the maintenance information required under Title 14 of the Code of Federal Regulations, Parts 43.16 and 91.409 is current, the revisions listed in Table 2 must be incorporated in Chapter 4 as they are issued.
Table 2. Original Issue - Mar 1/2009

Revision Number Date

1 Mar 1/2012

2. Export Compliance A. This publication contains technical data and is subject to U.S. export regulations. This information has been exported from the United States in accordance with export administration regulations. Diversion contrary to U.S. law is prohibited.
ECCN: 9E991



## LIST OF REVISIONS Page 1 © Cessna Aircraft Company Jul 1/2012

# CHAPTER 

# 2 **0**

**STANDARD PRACTICES -**  **AIRFRAME**

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL



## LIST OF EFFECTIVE PAGES

CHAPTER-SECTION-SUBJECT PAGE DATE
20-Title 20-List of Effective Pages 20-Record of Temporary Revisions
20-Table of Contents 20-00-00 Page 1 Feb 1/2009 20-05-00 Pages 201-213 Feb 1/2009 20-10-00 Pages 201-214 Feb 1/2009 20-20-00 Pages 201-209 Feb 1/2009 20-30-00 Pages 201-208 Feb 1/2009 20-50-00 Pages 1-3 Jan 1/2012 20-70-00 Pages 201-213 Jan 1/2012 20-80-00 Page 201 Feb 1/2009 20-90-00 Pages 201-213 Feb 1/2009 20-95-00 Pages 1-5 Jul 1/2012 20-95-02 Pages 1-2 Jul 1/2012



## 20 - LIST OF EFFECTIVE PAGES Page 1 of 1 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL



## CONTENTS
STANDARD PRACTICES AIRFRAME - GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-00-00 Page 1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-00-00 Page 1 Material and Tool Cautions - General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-00-00 Page 1 TORQUE DATA - MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-05-00 Page 201 Torque Data - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-05-00 Page 201 SAFETYING - MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-10-00 Page 201 Safetying - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-10-00 Page 201 Safety Wiring Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-10-00 Page 201 Twisting with Special Tools. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-10-00 Page 204 Securing Oil Caps, Drain Cocks, and Valves. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-10-00 Page 204 Proper Securing of Fittings. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-10-00 Page 206 Securing With Cotter Pins. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-10-00 Page 206 CONTROL CABLES AND PULLEYS - MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . 20-20-00 Page 201 Control Cable Wire Breakage And Corrosion Limitations. . . . . . . . . . . . . . . . . . . . . . . . 20-20-00 Page 201 Cable System Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-20-00 Page 205 Corrosion and Rust Prevention . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-20-00 Page 208 Cable Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-20-00 Page 208 Cable Tension Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-20-00 Page 208 STANDARD PRACTICES AIRFRAME - MAINTENANCE PRACTICES. . . . . . . . . . . . . . . . 20-30-00 Page 201 Turnbuckles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-30-00 Page 201 Turnbuckle Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-30-00 Page 201 Witness Hole . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-30-00 Page 201 Safety Methods for Turnbuckles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-30-00 Page 201 Secured Safety-Wired Turnbuckles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-30-00 Page 202 Special Locking Devices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-30-00 Page 205 SOLVENTS, SEALANTS, AND ADHESIVES - DESCRIPTION AND OPERATION . . . . . 20-50-00 Page 1 Solvents, Sealants, and Adhesives . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-50-00 Page 1
LIGHTNING PROTECTION AND STATIC DISSIPATION SYSTEMS - MAINTENANCE PRACTICES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-70-00 Page 201 Lightning Protection and Static Dissipation Systems. . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-70-00 Page 201 Inspection and Repair After Lightning Strike . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-70-00 Page 206 Checkout Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-70-00 Page 208 Repair of Static Wicks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-70-00 Page 211 REPAIR OF CLICKBOND NUTPLATES - MAINTENANCE PRACTICES . . . . . . . . . . . . . . 20-80-00 Page 201 Repair of Clickbond Nutplates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-80-00 Page 201 SWAGELOK FITTINGS - MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-90-00 Page 201 Swagelok Fittings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-90-00 Page 201 TAP TESTING - DESCRIPTION AND OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-95-00 Page 1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-95-00 Page 1 Inspection Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-95-00 Page 1 Tap Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-95-00 Page 1 Required Chapter 4 Inspection Areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-95-00 Page 2
STRUCTURAL INSPECTIONS - DESCRIPTION AND OPERATION . . . . . . . . . . . . . . . . . . 20-95-02 Page 1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-95-02 Page 1 Visual Inspections. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-95-02 Page 1



## 20 - CONTENTS Page 1 of 1 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

TAP TESTING - DESCRIPTION AND OPERATION

1. General A. This section contains information needed to complete tap testing procedures on the airplane. Information required to complete inspections of specifi c locations on the airplane can be found in the applicable section for that area of structure.
2. Inspection Requirements A. Before the tap test inspection is started, you must comply with the following requirements: (1) You must have a blunt-ended tap hammer (or equivalent) that weighs 1.0 ounce, +0.3 or -0.3
ounce. (2) The inspector must be capable of distinguishing and differentiating audible pitch changes produced during the tap test. (3) The airplane must be moved to an area free from loud noise produced by traf fi c, power equipment, aircraft or any other source that would require raised voices for normal conversation.
3. Tap Testing A. Complete a Tap Test of the applicable structure. (1) Thoroughly clean and dry the inspection surface to remove any loose dirt, contaminates and grease. (2) Complete the tap test with the use of a blunt-ended tap hammer or equivalent with a head that weighs 1.0 ounce, +0.3 or -0.3 ounce.



### CAUTION: Do not use excessive or aggressive force or a hammer with a sharp edge to strike the surface of the airplane. Structural damage will occur if too much force or a sharp-edged hammer is used to complete the tap test.
(3) Use gentle and consistent force with the tap hammer to lightly tap the surface in each 1-inch 2 area throughout the inspection zone. (4) Compare similar structures within the inspection zone for changes in the acoustic response pitch.

NOTE: Areas of the fuselage that have structure behind them will have a higher response pitch than areas that do not have structure behind them.
(5) A "fl at" or "dead" response pitch is considered unacceptable. (6) Larger areas that are disbonded or delaminated can cause the tap hammer to rebound to a lower height than it would on intact structure. (7) Use moderate pressure from your hand or several fi ngers to push on an area of structure. (a) A faint "crackling" sound can often be heard if the area has core damage.



## 20-95-00 Page 1 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

(8) Put a mark on damaged areas to indicate the location and size of the area where the damage is found. (9) Put a mark on any areas where you are uncerta in whether damage exists to indicate that the area is suspect. Additional Nondestructive Inspection (NDI) procedures must be completed to evaluate the area more closely. (10) Cessna recommends that maintenance personnel that complete tap tests be composite repair technicians trained in accordance with SRM standards or certifi ed NDI technicians.
4. Required Chapter 4 Inspection Areas A. The inspections listed in Chapter 4 require that tap testing be completed in the following areas: (1) Fuselage Bonding Seams - The fuselage halves are split into left and right symmetrical sides and include the areas from the fi rewall back to and including the vertical stabilizer. The seam extends from centerline to 2 inches on the right side of centerline. The seam tapers to 1.75 inches at approximately FS 240 and tapers again to 1.5 inches at approximately FS 261.5. The upper fuselage bond seam from the top of the windshield to a point 48 inches aft of the top of the windshield is an area of extremely thick ply buildup and can not be effectively tap tested. This area is only to be visually inspected. (2) Wing Skin Leading Edge and Trailing Edge Seams - The wing skin seams are at the leading and trailing edges of the wing. The leading edge seam is 2 inches wide and centered about the leading edge. The trailing edge s hould be tap tested on the top and bottom of the edge from the edge to 2 inches inboard. (3) Wing Skin to Ribs and Spars - The location of each rib and spar is shown in Section 57-10-00, Location of Spars and Ribs. The top and bottom wing skin at the areas of the ribs and spars should be tap tested. (4) Wing Flaps Leading and Trailing Edge Seams - The fl ap seams are at the l eading and trailing edges of the fl ap. The leading edge is 1 inch wide and extends 1 inch up from the leading edge chord plane of the fl ap. Because the bond extends onto core as shown in Figure 1, tap testing is only valid for the fi rst 0.5 inch of the bond. The trailing edge should be tap tested on the top and bottom of the edge from the edge to 1.5 inches forward. (5) Aileron Leading and Trailing Edge Seams - The aileron seams are at the leading and trailing edges of the ailerons. The leading edge seam is 1.0 inch wide starting 1 inch along the surface from the leading edge of the aileron. In the area around the drive hinge attachment pocket, tap test approximately 1.0 inch from the edge of the part to verify the bonding surface. The trailing edge should be tap tested on the top and bottom of the trailing edge from approximately 0.90 inch from the edge to approximately 2.0 inches from the trailing edge as shown in Figure 2. (6) Rudder Leading and Trailing Edge Seams - The rudder seams are at the leading and trailing edges of the rudder. The leading edge seam is the width of the fl at leading edge of the rudder. The trailing edge seam should be tested as follows: (a) The top 14 inches should be tested by tapping on the right hand side a distance of 1.5 inches inboard from the trailing edge. (b) The remainder of the trailing edge should be tested 1.0 inch inboard from the trailing edge. Refer to Figure 3 for areas of tap testing.



## 20-95-00 Page 2 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

Wing Flap Leading Edge Tap Testing Area Figure 1 (Sheet 1)


## 20-95-00 Page 3 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

Aileron Tap Test Areas Figure 2 (Sheet 1)


## 20-95-00 Page 4 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

Rudder Tap Test Areas Figure 3 (Sheet 1)


## 20-95-00 Page 5 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

STRUCTURAL INSPECTIONS - DESCRIPTION AND OPERATION

1. General A. This section contains information needed to complete inspections on the structure of the airplane. The procedures given here are the general requirements that must be followed to correctly complete inspections. More specifi c information relating to the area that is to be inspected can be found in the inspection procedure for each component or area of the airplane.
2. Visual Inspections A. Equipment. (1) The following equipment can be used to complete required visual inspections. Not all equipment is required for each inspection and additional tools or equipment can be required for inspections of specifi c areas of the airplane: • Flashlight or other light source capable of producing 100 foot-candles at the inspection surface • Inspection mirror • Borescope • Camera or camcorder
B. Personnel. (1) The following are requirements that the inspector must meet to complete visual inspections of the airplane structure and components: • Near Vision of 20/25 (Snellen) at 16 inches +1 or -1 inch or equivalent, in at least one eye, natural or corrected • Capable of distinguishing and differentiating colors • Familiar with the appearance of visible damage and have training and experience on visual inspection of aircraft structure C. Access Requirements. (1) Direct visual examination must be used whenever possible. For areas that are not accessible, the use of a borescope or digital camera or camcorder attached to a pole is recommended. (2) The examination must be completed at a distance of not more than 24 inches from the surface of the component that is to be inspected. (3) The examination must be completed at an angle that is within 30 degrees of perpendicular to the surface that is to be inspected. D. Visual Inspection Procedure. (1) Clean the inspection surfaces thoroughly to remove all loose materials, dirt, contamination and grease. (2) Use a towel to dry the inspection surface. (3) Use a light source held approximately perpendicular to the inspection surface to examine the structure or component. (4) Use a light source held and an angle of approximately 15 degrees of parallel with the inspection surface to examine the structure or component. (5) Examine the structure or components for the following: • Paint that is blistered, swollen, cracked, deformed or missing • Security of parts or attached components • Discoloration • Bucking • Bulging • Dents • Oil-canning • Wrinkles • Chafi ng • Foreign objects • Fluid leaks. (6) Put a mark on any damaged areas that shows the location and type of damage found.



## 20-95-02 Page 1 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

(7) Put a mark on any areas where you are uncerta in whether damage exists to indicate that the area is suspect.



## 20-95-02 Page 2 © Cessna Aircraft Company Jul 1/2012

# CHAPTER 

# 5 **3**

**FUSELAGE**

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL



## LIST OF EFFECTIVE PAGES

CHAPTER-SECTION-SUBJECT PAGE DATE
53-Title 53-List of Effective Pages 53-Record of Temporary Revisions
53-Table of Contents 53-00-00 Page 1 Feb 1/2009 53-10-00 Pages 1-4 Feb 1/2009 53-30-00 Pages 1-2 Feb 1/2009 53-50-00 Page 1 Feb 1/2009 53-60-00 Pages 1-2 Feb 1/2009 53-70-00 Pages 201-202 Feb 1/2009 53-70-00 Pages 501-503 Jul 1/2012



## 53 - LIST OF EFFECTIVE PAGES Page 1 of 1 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL



## CONTENTS
FUSELAGE - GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-00-00 Page 1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-00-00 Page 1
FUSELAGE AND PRIMARY STRUCTURE - DESCRIPTION AND OPERATION . . . . . . . 53-10-00 Page 1 Identifi cation and Inspection of Fuselage Components . . . . . . . . . . . . . . . . . . . . . . . . . . 53-10-00 Page 1 Painting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-10-00 Page 1 Lightning Strike Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-10-00 Page 1 Fuselage Primary Structure Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-10-00 Page 1 FUSELAGE ACCESS - DESCRIPTION AND OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . 53-30-00 Page 1 Fuselage Access Panels. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-30-00 Page 1 AERODYNAMIC FAIRINGS - DESCRIPTION AND OPERATION. . . . . . . . . . . . . . . . . . . . . 53-50-00 Page 1 Aerodynamic Fairings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-50-00 Page 1 CONTROL SYSTEM SUPPORTS - DESCRIPTION AND OPERATION . . . . . . . . . . . . . . . 53-60-00 Page 1 Control System Supports . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-60-00 Page 1 FUSELAGE COMPONENTS - MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . 53-70-00 Page 201 Removal, Installation, and Maintenance Practices for Fuselage Components . . . . . 53-70-00 Page 201 FUSELAGE COMPONENTS - ADJUSTMENT/TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-70-00 Page 501 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-70-00 Page 501 Aft Fuselage Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53-70-00 Page 501



## 53 - CONTENTS Page 1 of 1 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

FUSELAGE COMPONENTS - ADJUSTMENT/TEST

1. General A. This section gives the information needed to complete the inspection of fuselage components and related structural components. For additional information on the fuselage structure, refer to Section 53-00-00, Fuselage - General.
2. Aft Fuselage Inspection A. Complete an inspection of the aft fuselage. (1) Remove the horizontal stabilizers. Refer to Section 55-10-00, Horizontal Stabilizer - Maintenance Practices. (2) Remove the aft baggage bulkhead access panel and the antenna bulkhead access panel. Refer to Section 53-30-00, Fuselage Access - Description and Operation. (3) Remove the air outlet vent access panel from below the right horizontal stabilizer. Refer to Section 53-30-00, Fuselage Access - Description and Operation. (4) Thoroughly clean and dry the inspection surface on the exterior skin of the aft fuselage to remove any loose dirt, contaminates and grease. (5) Complete a visual inspection of the left and right aft fuselage exterior skin surfaces shown in Figure 501. (a) Inspections must be completed in accordance with Section 20-95-02, Structural Inspections - Description and Operation. (b) Put a mark on damaged areas to indicate the location and size of the area where the damage is found. (c) Put a mark on any areas where you are uncertain whether damage exists to indicate that the area is suspect. (6) Complete a visual inspection of the left and right aft fuselage interior skin surfaces shown in Figure 501 that are visible through the air outlet vent panel and through the aft baggage bulkhead access panel. (a) Inspections must be completed in accordance with Section 20-95-02, Structural Inspections - Description and Operation. (b) Use of a borescope or digital camera attached to a pole is recommended for areas that are not visible to the technician. (c) Put a mark on damaged areas to indicate the location and size of the area where the damage is found. (d) Put a mark on any areas where you are uncertain whether damage exists to indicate that the area is suspect. (7) Complete a tap test of the left and right aft fuselage exterior skin surfaces that are within a 7-inch radius of the leading edge of the horizontal stabilizers. Refer to Figure 501. (a) The tap test must be completed in accordance with Section 20-95-00, Tap Testing - Description and Operation as well as the instructions that follow:


### CAUTION: Do not strike the fuselage with a sharpened hammer or any other tool that has sharp edges. Fuselage damage can result if a blunt-ended tap hammer or equivalent is not used.
(b) Use a blunt-ended tap hammer or equivalent with a head that weighs 1.0 ounce, +0.3 or -0.3 ounce to lightly tap the fuselage in each 1-inch 2 area throughout the inspection zone. (c) Compare similar structures within the inspection zone for changes in the response pitch. 1 Areas with structure under the skin will have a higher pitch response than areas where there is no structure under the skin. Refer to Figure 501 to see areas that have structure under the skin. (d) The inspection area is 2 plies thick (less than 0.020 inch), except for a 4-ply band that is located 5.0 inches above to 4.0 inches below th e chord of the horizontal stabilizer. This 4-ply band extends forward and aft through the entire inspection zone. (e) A "fl at" or "dead" pitch response is considered unacceptable.



## 53-70-00 Page 501 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

Aft Fuselage Inspection Zone Figure 501 (Sheet 1)


## 53-70-00 Page 502 © Cessna Aircraft Company Jul 1/2012

### CESSNA AIRCRAFT COMPANY 

## MODEL LC40-550FG MAINTENANCE MANUAL

(f) Put a mark on damaged areas to indicate the location and size of the area where the damage is found. (g) Put a mark on any areas where you are uncertain whether damage exists to indicate that the area is suspect. (h) If any damage is found or if there are suspect areas that have not been proven to be acceptable, contact Cessna Customer Service by phone or fax at the following numbers: 1 Phone: 316-517-5800 2 Fax: 316-517-7271 (8) Install the aft baggage bulkhead access panel and the antenna bulkhead access panel. Refer to Section 53-30-00, Fuselage Access - Description and Operation. (9) Install the air outlet vent access panel on the right horizontal stabilizer. Refer to Section 53-30- 00, Fuselage Access - Description and Operation. (10) Install the horizontal stabilizers. Refer to Section 55-10-00, Horizontal Stabilizer - Maintenance Practices.



## 53-70-00 Page 503 © Cessna Aircraft Company Jul 1/2012