AD 84-22-01

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AD Number:
84-22-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; VICKERS-SLINGSBY Model T65A Gliders
Subject:
Elevator Malfunction
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/07/1984
Make:
Vickers-Slingsby
Model:
T.65A Vega
Product Type:
Aircraft
Product Subtype:
Glider
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 84-22-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4941

AD NUMBER:   84-22-01

SUBJECT HEADING:   Airworthiness Directives; VICKERS-SLINGSBY Model T65A Gliders

ACTION:  

SUMMARY:  

DATES:   Effective November 7, 1984.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
84-22-01 VICKERS-SLINGSBY: Amendment 39-4941. Applies to Model T65A gliders, all serial numbers certificated in any category.

Compliance required as indicated.

To prevent possible malfunction of the elevator, accomplish the following:

1. Within the next 10 hours time in service, after the effective date of this AD, unless already accomplished, inspect the following in accordance with Slingsby Engineering Ltd. (S.E.L.) Technical Instruction (TI) No. 104/T65, Issue 1, Section 1, dated September 22, 1982 (hereinafter referred to as TI):

A. The pivot bearing (P/N 04DU04) for the elevator rocker arm assembly on top of the fin for wear,

B. The glass reinforced plastic operating tongue of the elevator which projects forward into the tailplane for cracks, damage, or lack of stiffness, and,

C. The tailplane center hinge pin mounting rib at the section just forward of the hinge pin for cracks and/or damage.

2. Prior to further flight:

A. If wear is found in excess of 0.01 inches in the forward and aft direction as a result of the inspection of Item 1A above, repair in accordance with Section 3 of the TI described in Item 1.

B. If cracks, damage or lack of stiffness are found as a result of the inspection of Item 1B above, repair in accordance with Section 2 of the TI described in Item 1.

C. If cracks or damage are found as a result of the inspection of Item 1C above, replace with a new reinforced rib in accordance with Section 4 of the TI described in Item 1.

3. Within the next 100 hours time in service, if cracks or damage are not found, unless already accomplished, reinforce the elevator in accordance with Section 5 of the TI described in Item 1.

4. Alternate inspections, adjustment of the inspection interval, or other actions which provide an equivalent level of safety must be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium, telephone 513.38.30 Ext. 2710.

The Slingsby Engineering Ltd. (S.E.L.) Technical Instruction (TI) No. 104/T65, Issue 1, dated September 22, 1982, identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request from Slingsby Engineering Limited, Ings Lane, Kirbymoorside, York Y066EZ, England. This document may also be examined at the Office of Regional Counsel, 12 New England Executive Part, Burlington, Massachusetts 01803.

This amendment becomes effective November 7, 1984.

FOOTER: