AD 83-03-05

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AD Number:
83-03-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Britten-Norman Model BN-2A MK III Trislander Series Airplanes
Subject:
Undercarriage Shock Absorber
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/22/1983
Make:
B-N Group Ltd.
Model:
BN2A MK. III | BN2A MK. III-2 | BN2A MK. III-3
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Superseded AD: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Superseded By: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: 83-03-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4565

AD NUMBER:   83-03-05

SUBJECT HEADING:   Airworthiness Directives; Britten-Norman Model BN-2A MK III Trislander Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 22, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
83-03-05 BRITTEN-NORMAN LTD: Amendment 39-4565. Applies to Model BN-2A MK III Trislander (all serial numbers) airplanes certificated in any category.

COMPLIANCE: Required as indicated, unless already accomplished.

To prevent the main undercarriage shock absorber support ring from separating from the inside of the undercarriage extension tube, accomplish the following:

a) Within the next 50 landings on airplanes which have accumulated 3,000 landings or more on the effective date of this AD, or prior to the accumulation of 3,050 landings on airplanes that have less than 3,000 landings on the effective date of this AD, and thereafter at intervals not to exceed 1,000 landings:

1) Visually inspect the rivets retaining the main undercarriage shock absorber internal support ring to the main undercarriage leg extension tube in accordance with Steps 1 through 4 of the "Inspection" Section of Britten-Norman Service Bulletin BN-2/SB.139, Issue 1, dated January 29, 1980 (hereinafter referred to as the Service Bulletin).

2) If one or more loose rivets are found during the above inspection, before further flight, replace all three rivets in accordance with Steps 1 through 3 of the "Rectification" Section of the Service Bulletin.

b) Within the next 50 landings on airplanes which have accumulated 15,000 landings or more on the effective date of this AD or prior to the accumulation of 15,050 landings on airplanes which have less than 15,000 landings on the effective date of this AD, replace all three rivets in accordance with Steps 1 through 3 of the "Rectification" Section of the Service Bulletin.

c) In the event that landings have not been recorded, 1,000 hours time-in-service may be used in place of 3,000 landings for purposes of complying with this AD.

d) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

e) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium.

This amendment becomes effective on February 22, 1983.

FOOTER: