AD 88-13-03 R1

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AD Number:
88-13-03 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CESSNA Model S550 Series Airplanes
Subject:
Cotter Pins - Main Landing Gear
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/15/1989
Make:
Cessna Aircraft Company
Model:
S550
Product Type:
Aircraft
Product Subtype:
Small/Large 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Superseded AD: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Superseded By: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: 88-13-03 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6135

AD NUMBER:   88-13-03 R1

SUBJECT HEADING:   Airworthiness Directives; CESSNA Model S550 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 15, 1989.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
88-13-03 R1 CESSNA: Amendment 39-5946 as amended by Amendment 39-6135.

Applicability: Model S550 series airplanes, Serial Numbers S550-0001 through S550-0158, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent loss of control of the airplane during landing or takeoff due to failure of the cotter pins securing the main landing gear torque link connections, accomplish the following:

A. Within 48 hours after the effective date of this AD, incorporate the following into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM:

"Prior to the first flight of each day, verify that the cotter pins securing the left and right main landing gear torque link connections are installed. If either cotter pin is broken, missing, or exhibits any evidence of being cut or sheared by the nut, prior to further flight, accomplish paragraph B. of this AD."

B. If either cotter pin is broken, missing, or exhibits any evidence of being cut or sheared by the nut, the nut must be retorqued to 630 inch-pounds, then tightened to align the cotter pin(s) hole, up to a maximum torque of 810 inch-pounds, and a new cotter pin(s), P/N MS24665-287, installed. This must be accomplished in accordance with Cessna S550 Maintenance Manual Section 32-11-01, pages 403, 404, and 405.

C. Modification of the main landing gear torque link assemblies in accordance with Cessna Service Bulletin SBS550-32-5, dated August 26, 1988, constitutes terminating action for the requirements of paragraphs A. and B., above.

D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Wichita Aircraft Certification Office, FAA, Central Region.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, Kansas 67277. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas.

Airworthiness directive 88-13-03 (Amendment 39-5946) which was effective June 20, 1988, superseded AD 86-01-02 (Amendment 39-5237) which was effective March 7, 1986, to all persons except those to whom it was made immediately effective by Priority Letter AD 86-01-02 dated January 6, 1986.

This amendment (39-6135, AD 88-13-03 R1) becomes effective March 15, 1989.

FOOTER: