AD 80-05-01

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AD Number:
80-05-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Weatherly Model 201C Series Airplanes
Subject:
Tail Cone Attach Fittings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/03/1980
Make:
Weatherly Aircraft Company
Model:
201C
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Superseded AD: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Superseded By: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: 80-05-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3704

AD NUMBER:   80-05-01

SUBJECT HEADING:   Airworthiness Directives; Weatherly Model 201C Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 3, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   80-05-01 WEATHERLY AVIATION COMPANY, INC.: Amendment 39-3704. Applies to all Model 201C series airplanes certificated in all categories.

Compliance is required as indicated unless already accomplished.

To prevent possible failure of the aft fuselage attach provisions, accomplish the following:
(a) Within 50 hours' time in service from the effective date of this AD, visually inspect with at least 2X magnification the four P/N 40352-9 and 40352-10 tail cone attach fittings for evidence of cracking, particularly in the bend radii and in the area of the bend relief hole.
NOTE: Weatherly Aviation Company, Inc. Service Note No. 10, dated January 23, 1980, refers to this subject.

(b) If cracks are found, replace the cracked fittings with P/N 40352-19 or 40352-20 fittings prior to further flight.

(c) Repeat the visual inspection of P/N 40352-9 and 40352-10 fittings required in paragraph (a) of this AD at intervals not to exceed 100 hours' time in service since the last inspection. Repetitive inspections required by this paragraph of this AD may be terminated when replacement of fittings with P/N 40352-19 and 40352-20 fittings is accomplished.

(d) Whenever cracks or other damage have been found in the welded tube tail frame, which mounts the tail wheel spring, inspect the tail cone attach fittings per paragraph (a) of this AD prior to further flight.

(e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.

This amendment becomes effective March 3, 1980.

FOOTER: