AD 58-10-03

AD Final Rules - DRS_58-10-03.html
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AD Number:
58-10-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Universal Models GC-1A and GC-1B Aircraft
Subject:
Landing Gear Stop Ring
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
Swift Museum Foundation, Inc.
Model:
GC-1A | GC-1B
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Superseded AD: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Superseded By: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: 58-10-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   58-10-03

SUBJECT HEADING:   Airworthiness Directives; Universal Models GC-1A and GC-1B Aircraft

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   58-10-03 UNIVERSAL: Applies to All Models GC-1A and GC-1B Aircraft With Adel Precision Products Corporation Landing Gears With Forged Aluminum Torque Knees.

(This AD is issued to clarify, add a 100-hour periodic inspection, and supersede AD 57- 13-07.)

Compliance required as indicated.

Failures have been reported of the stop ring brazed to the inner piston strut. Failures resulted in the piston sliding out of the strut and the torque knees assuming a straight position. This overextension of the strut precludes gear retraction into the wheel well.

1. Within the next 100 hours of operation, unless already accomplished, a suitable external stop or some other equivalent means should be provided which will function as a safety measure in case of failure of the internal stop ring.

At the time of installation of the external stop, or within the next 100 hours of operation if not already accomplished, the Adel strut assembly stop ring is to be examined for condition and rejected if the stop ring is loose or shows signs of separation at the braze. After reassembly, the external stop must be installed so that there exists a clearance of 1/32 to 1/8 inch between the face of the stop and side of the strut cylinder with the gear fully extended. In the event there is insufficient clearance, the external stop must be reworked until the proper clearance is obtained.

2. At each subsequent 100 hours of operation, the clearance is to be rechecked with the strut fully extended. If there is no clearance between the external safety stop and the strut cylinder, it will be necessary to disassemble the strut and examine the internal stop ring for indications of failure. If failure of the stop ring is apparent, the inner cylinder assembly, Adel P/N 16084, must be replaced or suitably reworked.

(Universal Aircraft Industries Customer Service Maintenance Bulletin No. 34 with Revision No. 1 covers this same subject.)

This supersedes AD 57-13-07.

FOOTER: