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C I R R U S
A I R P L A N E M A I N T E N A N C E M A N U A L
1. GENERAL
This Chapter contains standard practices for the maintenance and repair of composite structures for Cirrus
aircraft and components. The objective governing all recommendations in the following procedures is to
restore the composite structure to its original level of strength and durability.
The general procedure for using the Chapter 51 - Standard Practices: Structures is as follows:
The extent of damage is determined using the methods outlined in Section 10 - Investigation, which
contains guidance for identification of damage and associated classifications.
Processes and methods used in the repair of the aircraft are described in Section 20 - Processes.
(Refer to 51-20)
Approved materials and equipment necessary to perform standard repairs are contained in Section 30
- Materials. Prior to each repair process, a table listing all necessary tools, equipment, and supplies is
provided.
(Refer to 51-30)
Section 70 - Standard Repairs contains specific composite repair procedures that are used with the
supporting processes outlined in Section 20.
Prior to each repair process, a table listing all necessary tools, equipment, and supplies is provided.
For information related to safety equipment refer to Section 00 - Standard Practices: Structures.
to 51-00)
A discussion on personnel qualifications, description of the primary structural components, Airframe Zone
Diagrams outlining the principal repair areas, and a definition of terms used in this Chapter are included
below.
EFFECTIVITY:
All

STANDARD PRACTICES: STRUCTURES

(Refer to 51-70)
M O D E L S R 2 0
(Refer to 51-10)
(Refer
51-00
Page 1
15 Jun 2010

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Summary of Contents for Cirrus SR20

  • Page 1 STANDARD PRACTICES: STRUCTURES 1. GENERAL This Chapter contains standard practices for the maintenance and repair of composite structures for Cirrus aircraft and components. The objective governing all recommendations in the following procedures is to restore the composite structure to its original level of strength and durability.
  • Page 2 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 A.
  • Page 3 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Clothing A resin proof apron should be worn when the situation demands that level of care.
  • Page 4 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 B.
  • Page 5 Direct chemical attack. (i.e. spilled battery acid) and Electrochemical attack which requires a medium. (usually water) Forms of Corrosion Contact Cirrus Design for disposition. (Refer to AMM-Intro-) Conditions Affecting Corrosion Contact Cirrus Design for disposition.
  • Page 6 (EMM) used in the electrical bonding of the aircraft. CAUTION: Contact Cirrus Design before attempting to repair any composite structure within the shaded no-repair zones. (Refer to AMM-Intro-)
  • Page 7 Repair plies are laid up alternately +45° and -45° from the 0° reference unless orientation is specifically defined in this section or as a part of a Cirrus authorized field repair instruction. Generally, the thickness of one ply is 0.008 - 0.010 inch (0.203 - 0.254 mm). To verify, or if no value is found in the ply lay-up tables, determine ply count by dividing measured laminate thickness by 0.009 inch (0.229 mm).
  • Page 8 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 90°...
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  • Page 21 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 197.5 212.5 90°...
  • Page 22 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 197.5 212.5 90°...
  • Page 23 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 90°...
  • Page 24 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 54.9 54.9 90°...
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  • Page 26 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 54.9 54.9 90°...
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  • Page 34 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 MAIN GEAR UPPER STRUT FAIRING LEFT SIDE SHOWN MAIN GEAR UPPER STRUT FAIRING RIGHT SIDE OPPOSITE LEGEND...
  • Page 35 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 WL 134.0 WL 130.0 WL 120.0...
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  • Page 37 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 F.
  • Page 38 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Bondline The sum of the thicknesses of the bondlines in a shimmed bond joint.
  • Page 39 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Cure To permanently change the properties of a resin system by controlled chemical reaction.
  • Page 40 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Filler A relatively inert substance added to a material to alter its physical, mechanical, thermal, electrical, and other properties.
  • Page 41 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Lamination The process of preparing a laminate.
  • Page 42 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Release Film An impermeable layer of film that does not bond to the resin being cured.
  • Page 43 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 Storage Life The time in storage over which the material maintains its mechanical properties as defined by the specification.
  • Page 44 C I R R U S A I R P L A N E M A I N T E N A N C E M A N U A L M O D E L S R 2 0 51-00 EFFECTIVITY: Page 44...

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