AD 78-20-11

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AD Number:
78-20-11
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Taylorcraft Models BC-12D and F-19
Subject:
Aileron Control Malfunction
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/16/1978
Make:
Taylorcraft 2000, LLC
Model:
BC12-D | F19
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Superseded AD: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Superseded By: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: 78-20-11
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3314

AD NUMBER:   78-20-11

SUBJECT HEADING:   Airworthiness Directives; Taylorcraft Models BC-12D and F-19

ACTION:  

SUMMARY:  

DATES:   Effective October 16, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   78-20-11 TAYLORCRAFT: Amendment 39-3314. Applies to Model BC-12D, Serial Nos. 6923, 8376, 8444, 8570, and 10538, and Model F-19, Serial Nos. F-080 through F-105, F- 107 through F-112 and F-115 through F-126 certificated in all categories.

To prevent malfunction of the aileron controls, accomplish the following:

(a) Inspect the two aileron stop pins (Taylorcraft P/N A-235) of the aileron control assembly (Taylorcraft P/N A-A231) prior to next 10 hours time in service after the effective date of this AD or by December 1, 1978, whichever occurs first. The assembly is located on the left side of the control column at the forward end of the control shaft and universal joint. Determine whether the stop pins are AN393-9 clevis pins as follows: Remove the deck panel (above instrument panel) and set control wheel in neutral position. In this position aileron stop pins will be on top. The proper pins (2) are identified by the flat head of the pins against front face of the sprocket. The flat head is cut partially to clear chain and obtain smooth operation of control. The shank of the stop protrudes approximately 1/4". If the sprocket has AN393-9 clevis pins, no further action is necessary.

(b) If the pins are made from 3/16" diameter rod (no head), inspect for the following:

(1) Bent pins

(2) Loose pins

(3) Inadequate protrusion (less than 1/4") of pin through aft of sprocket or improper functioning.

(c) If any of the conditions identified in (b) above are present, replace the sprocket prior to further flight.

(d) If the AN393-9 clevis pin is not installed and none of the three conditions in (b) are found, replace the sprocket within 50 flight hours or by May 1, 1979 with a sprocket in which clevis pins (AN393-9) have been installed. Until the sprocket is replaced, reinspect within 10 hours time in service from last inspection. A proper sprocket may be obtained from Taylorcraft Aviation Corporation, 14600 Commerce N.E., P.O. Box 243, Alliance, Ohio 44601.

Taylorcraft Bulletin Number 78-002 dated September 19, 1978 also applies to the subject matter of this AD.

This amendment becomes effective October 16, 1978.

FOOTER: