AD 81-07-11 R1

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AD Number:
81-07-11 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Cessna Model 335, 340 and 340A Airplanes
Subject:
Balance Weight Support Structure
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/17/1981
Make:
Cessna Aircraft Company
Model:
335 | 340 | 340A
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 81-07-11 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4096

AD NUMBER:   81-07-11 R1

SUBJECT HEADING:   Airworthiness Directives; Cessna Model 335, 340 and 340A Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 17, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
81-07-11 R1 CESSNA: Amendment 39-4078 as amended by Amendment 39-4096. Applies to Model 335 (S/N 335-0001 thru 335-0065), Model 340 (S/N 340-0001 thru 340-0555) and Model 340A (S/N 340A0001 thru 340A1203) airplanes certificated in any category.

COMPLIANCE: Required as indicated, unless already accomplished.

To ensure the integrity of the elevator balance weight support structure and specified components of the horizontal stabilizer, accomplish the following:

A) Prior to further flight and at each l0 hours time-in-service interval thereafter, accomplish the following in accordance with Cessna Multi-engine Customer Care Service Information Letter ME79-44, Revision 5, dated September 29, 1980:

1. On all airplanes, remove the elevator tip covers and visually inspect the elevator balance weights for looseness.

a. On all Models 335 and 340 airplanes and on Model 340A (S/Ns 340A0001 thru 340A1038) airplanes, visually inspect the P/N 0832250-4, -33 and -75 ribs, and P/N 0832000-61, -62 gussets for cracks and/or loose rivets.

b. On Model 340A (S/Ns 340A1039 thru 340A1203) airplanes, visually inspect the P/N 832250-100 and -33 ribs, P/N 5334108-2 channel, -3 spar extension and -4 gussets for cracks and/or loose rivets.

2. Visually inspect the horizontal stabilizer outboard hinge bracket assembly (on Models 340 (all S/Ns) and 340A (S/Ns 340A0001 through 340Al035), the P/N is 5132013-5; on Model 340A (S/Ns 340A1036 thru 340Al203) the P/N is 5132013-10; and on Model 335 (all S/Ns) the P/N is 5132013-7), the outboard hinge bearing, the aft spar, and the tip ribs for cracks, loose rivets, or signs of chafing.

3. Prior to further flight, replace any defective parts found during any inspection required by this AD with airworthy parts of the same part number.

B) Within 24 hours following any inspection specified by paragraph A), the owner/operator must submit a written report of any cracks, loose rivets, or signs of chafing discovered during any inspection required by this AD to the Federal Aviation Administration, Aircraft Certification Program, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209. (Reporting approved by the Office of Management and Budget Order 0MB No. 04-R0174.)

C) On or before December 15, 1981, replace the horizontal tail in accordance with Cessna Service Kit Instructions SK 340-24, dated March 16, 1981, and Cessna Service Kits SK 340-24-1, -2, or -3, and SK 340-19, as appropriate. After installation of the appropriate Cessna Service Kit(s), the requirements of paragraphs A) and B) of this AD are no longer applicable.

D) Airplanes may be flown in accordance with FAR 21.197 to a location where the provisions of paragraph C) of this AD can be accomplished.

E) Any equivalent method of compliance with this AD must be approved by the Chief, Aircraft Certification Program Office, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 942-4285.

This AD supersedes AD 80-21-04, Amendment 39-3959.

Amendment 39-4078 became effective April 13, 1981.

This amendment 39-4096 becomes effective April 17, 1981.

FOOTER: