AD 81-09-04

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AD Number:
81-09-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; SHORT BROTHERS LIMITED Model SD3-30 Series Airplanes
Subject:
Main Landing Gear Wheels
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/04/1981
Make:
Short Brothers PLC
Model:
SD3-30
Product Type:
Aircraft
Product Subtype:
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Superseded AD: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Superseded By: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: 81-09-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4093

AD NUMBER:   81-09-04

SUBJECT HEADING:   Airworthiness Directives; SHORT BROTHERS LIMITED Model SD3-30 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 4, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   81-09-04 SHORT BROTHERS LIMITED: Amendment 39-4093. Applies to Model SD3-30 series airplanes, with main landing gear wheel, P/N AH53369, installed, certificated in all categories.

Compliance is required as indicated, unless already accomplished.

To prevent failure of the main landing gear wheels, accomplish the following:

(a) Prior to the accumulation of 150 hours time in service or 250 landings after the effective date of this AD, whichever occurs sooner, and thereafter at intervals not to exceed 250 landings since the last inspection, inspect the valve side half, P/N AH43782 Mod State 1, of the main landing gear wheel, P/N AH53369, for cracks using the eddy current method in accordance with the Dunlop Component Maintenance Manual 32-40-65, Revision 6, dated May 11, 1979, or an FAA-approved equivalent.

(b) Prior to the accumulation of 300 hours time in service or 500 landings since new, or prior to the accumulation of 150 hours time in service or 250 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 250 landings since the last inspection, inspect the valve side half, P/N AH43782 Mod State 2, of the main landing gear wheel, P/N AH53369, for cracks using the eddy current method in accordance with the Dunlop Component Maintenance Manual 32-40-65, Revision 6, dated May 11, 1979, or an FAA-approved equivalent.

(c) If as a result of the inspection required in paragraph (a) or (b) of this AD, any crack or cracks are found, replace the wheel with a serviceable wheel of the same part number, or an FAA-approved equivalent and continue the repetitive inspection required by paragraph (a) or (b) of the AD as appropriate.

(d) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium.

NOTE: Shorts Service Bulletin SD3-32-64, Revision 2, dated January 25, 1980, and Dunlop Aviation Division Service Bulletin No. 32-920, Revision 2, dated November 16, 1979, refer to this subject.

This amendment becomes effective May 4, 1981.

FOOTER: