AD 79-03-05

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AD Number:
79-03-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Britten-Norman (Bembridge) LTD Model BN-2A Mk III Trislander Series Airplanes
Subject:
Main Landing Gear Extension Tube Assemblies
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/27/1979
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Superseded AD: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Superseded By: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: 79-03-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3412

AD NUMBER:   79-03-05

SUBJECT HEADING:   Airworthiness Directives; Britten-Norman (Bembridge) LTD Model BN-2A Mk III Trislander Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 27, 1979.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
79-03-05 BRITTEN-NORMAN (Bembridge) LTD: Amendment 39-3412. Applies to Model BN-2A Mk III Trislander series airplanes, certificated in all categories.

Compliance is required, as indicated, unless already accomplished.

To prevent structural failure of the main landing gear:

(a) Within the next 10 hours time in service after the effective date of this AD, inspect the shock absorber mounting flange, P/N NB-40-C-075, at attachment point to the lower extremity of the main landing gear leg extension tube, P/N NB-40-D-337, for sheared or loose rivets and general structural integrity in accordance with paragraph "ACTION" of Britten- Norman Service Bulletin BN-2/SB.118 (Service Bulletin), dated July 25, 1978, or an FAA- approved equivalent.

(b) If, during any inspection required by this AD, sheared or loose rivets or indications of movement of the mounting flange within the extension tube are found, before further flight, accomplish the appropriate rectification and modification in accordance with paragraph "Rectification/Modification" (Mod. NB/M/1007) of the Service Bulletin, or an FAA- approved equivalent.

(c) If, during the inspection required by paragraph (a) of this AD, no sheared or loose rivets or indications of movement of the mounting flange within the extension tube are found, the airplane may be returned to service and thereafter, prior to the accumulation of 200 hours time in service after the completion of the inspection required by paragraph (a) of this AD, accomplish the rectification and modification required by paragraph (b) of this AD.

(d) If, prior to the accomplishment of the rectification and modification required by this AD, the landing gear is abused, e.g., the aircraft experiences hard or rough landings, a blown tire, sharp turns pivoting about a braked wheel, or taxiing over rough or soft surfaces, before further flight, inspect the shock absorber mounting flange, P/N NB-40-C-075, at attachment point to the lower extremity of the main landing gear extension tube, P/N NB-40-D-337, for sheared or loose rivets and general structural integrity in accordance with paragraph "ACTION" of the Service Bulletin, or an FAA-approved equivalent.

(e) Within the next 10 hours time in service after the effective date of this AD, fabricate and install in the cockpit near the limitation placard a temporary placard, which must remain in place until the rectification and modification required by this AD are accomplished, which states:

CAUTION
1. Avoid sharp turns pivoting about a braked wheel.

2. Avoid taxiing over rough or soft surfaces.

3. Record any abuse of the landing gear, e.g., hard or rough landings, blown tire, sharp turns pivoting about a braked wheel, taxiing over rough or soft surfaces, in the aircraft maintenance log book or other appropriate maintenance record and have inspected in accordance with AD 79-03-05 prior to next flight.

4. These limitations must be observed until the modification required by AD 79-03- 05 is incorporated.

(f) Before installation on aircraft, incorporate Britten-Norman Mod. NB/M/1007 or an FAA-approved equivalent on main landing gear extension tube assemblies held as spares which do not already incorporate that modification.

This amendment becomes effective February 27, 1979.

FOOTER: