REVISION

MODEL LC42-550FG

MAINTENANCE MANUAL

REVISION 2

1 JULY 2012

350MM02

Please replace the current manual in its entirety.
Maintenance Manual

MODEL LC42-550FG

Member of GAMA

COPYRIGHT © 2009

CESSNA AIRCRAFT COMPANY

WICHITA, KANSAS, USA 1 FEBRUARY 2009

350MM02 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 LC42-550FG

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 - Feb 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 Certification

Office. 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 - Feb 1/2009

Revision Number Date 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

STANDARD

0

PRACTICES -

AIRFRAME
CESSNA AIRCRAFT COMPANY

MODEL LC42-550FG

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 201-212 Feb 1/2009

20-10-00 Pages 201-214 Feb 1/2009

20-20-00 Pages 201-210 Feb 1/2009

20-30-00 Pages 201-208 Feb 1/2009

20-50-00 Pages 201-202 Feb 1/2009

20-70-00 Pages 201-223 Feb 1/2009

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 LC42-550FG

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 203

Corrosion And Rust Prevention. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-20-00 Page 208

Cable Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-20-00 Page 208

Cable Tenison Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-20-00 Page 210

TURNBUCKLES - 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 - MAINTENANCE PRACTICES . . . . . . . . . . 20-50-00 Page 201

Solvents, Sealants, and Adhesives . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-50-00 Page 201

LIGHTNING PROTECTION AND STATIC DISSIPATION - 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 207

Checkout Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-70-00 Page 209

Repair of Static Wicks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-70-00 Page 222

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 LC42-550FG

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 specific 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 traffic, 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-inch2

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 "flat" 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 fingers 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 LC42-550FG

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 uncertain 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 certified 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 firewall 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 should 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 flap seams are at the leading and trailing

edges of the flap. The leading edge is 1 inch wide and extends 1 inch up from the leading edge

chord plane of the flap. Because the bond extends onto core as shown in Figure 1, tap testing

is only valid for the first 0.5 inches 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

inches 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 flat 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 inches inboard from the trailing

edge.

(c) Refer to Figure 3 for areas of tap testing.

20-95-00 Page 2

© Cessna Aircraft Company Jul 1/2012
CESSNA AIRCRAFT COMPANY

MODEL LC42-550FG

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 LC42-550FG

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 LC42-550FG

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 LC42-550FG

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 specific 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 specific 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

• Chafing

• 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 LC42-550FG

MAINTENANCE MANUAL

(7) Put a mark on any areas where you are uncertain whether damage exists to indicate that the

area is suspect.

20-95-02 Page 2

© Cessna Aircraft Company Jul 1/2012
CHAPTER

5

FUSELAGE

3
CESSNA AIRCRAFT COMPANY

MODEL LC42-550FG

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 LC42-550FG

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

Identification 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 LC42-550FG

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-inch2 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 the chord of the horizontal stabilizer. This

4-ply band extends forward and aft through the entire inspection zone.

(e) A "flat" or "dead" pitch response is considered unacceptable.

53-70-00 Page 501

© Cessna Aircraft Company Jul 1/2012
CESSNA AIRCRAFT COMPANY

MODEL LC42-550FG

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 LC42-550FG

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