AD 80-14-10

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AD Number:
80-14-10
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Britten-Norman Model BN-2A Mark III Series Airplanes
Subject:
Rudder Balance Arm Brackets
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/14/1980
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Superseded AD: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Superseded By: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: 80-14-10
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3828

AD NUMBER:   80-14-10

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

ACTION:  

SUMMARY:  

DATES:   Effective July 14, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-14-10 BRITTEN-NORMAN (BEMBRIDGE) LTD.: Amendment 39-3828. Applies to Model BN-2A Mark III Series Trislander airplanes, certificated in all categories.

Compliance is required as indicated unless already accomplished.

To detect corrosion and to prevent loss of the rudder mass balance arm brackets which could cause hazardous rudder flutter, accomplish the following:

(a) Within the next 25 hours time in service after the effective date of this AD or prior to 2 years since new, whichever occurs later, visually inspect for corrosion the support brackets of the mass balance arms at the top, and on each side, of the rudder in accordance with paragraph "ACTION," of Britten-Norman Service Bulletin BN-2/SB.116, dated June 5, 1978 (hereinafter referred to as the service bulletin), or an FAA-approved equivalent.

(b) If corrosion is found as a result of the inspection required by paragraph (a) of this AD, before further flight, except that the aircraft may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where the work can be performed, accomplish either of the following:

(1) Perform the permanent repair as specified in "Rectification - Part 1" of the service bulletin or an FAA-approved equivalent, and thereafter reinspect for corrosion in accordance with paragraph (a) of this AD, at intervals not to exceed 3 years from the date of the repair; or

(2) Perform the temporary repair as specified in "Rectification - Part 2" of the service bulletin or an FAA-approved equivalent, and thereafter continue to perform the inspection required by paragraph (a) of this AD, at intervals not to exceed 2 months from the date of the repair, for a maximum of 1 year at which time the permanent repair and inspection required by paragraph (b)(1) of this AD must be accomplished.

(c) If no external corrosion is found as a result of the inspection required by paragraph (a) of this AD, the mass balance arm support brackets may continue in service for a period not to exceed 6 months from the date of the initial inspection, provided that the visual inspection required by paragraph (a) of this AD is repeated at intervals not to exceed 2 months or 200 hours time in service from the last inspection, whichever occurs first, after which the permanent or temporary repairs and inspections of paragraph (b)(1) or (b)(2) must be accomplished.

(d) Prior to the installation of rudders held in stock as spares, accomplish the inspection and repair as necessary in accordance with paragraphs (a) and (b)(1) of this AD.

(e) For purposes of this AD, an FAA-approved equivalent must be approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, Telephone: 513.38.30.

This amendment becomes effective July 14, 1980.

FOOTER: