AD 48-19-03

AD Final Rules - DRS_48-19-03.html
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AD Number:
48-19-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS DC-6
Subject:
Elevator Trim Tab Operating Mechanism
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
The Boeing Company
Model:
DC-6 | DC-6A | DC-6B
Product Type:
Aircraft
Product Subtype:
Large 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Superseded AD: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Superseded By: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: 48-19-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   48-19-03

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS DC-6

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
48-19-03 DOUGLAS: Applies to DC-6 Serial Numbers 42854 Through 42896; 43000 Through 43024; 43035 Through 43052; 43055 Through 43058; 43061 Through 43064; and 43105 through 43110.

Compliance required by September 15, 1958.

Due to two failures in flight and to reported excessive looseness in the elevator trim tab operating mechanism, the following must be accomplished:

1. Rework drum, P/N 4344461 into drum, P/N 4357010-4, by boring hole in end of drum 0.8755-0.8745 diameter, 0.188-0.189 deep and concentric within 0.002 full indicator reading, and press in bushing 4357010-2 into hole. Remove nut, P/N 2335472, press in nut, P/N 2357008, in place so that two holes in nut match two holes in drum, P/N 4357010-4, and insert two pins, P/N 1335480, and stake in place. This rework changes jackshaft mechanism assembly, P/N 434460, into P/N 4357010.

2. Rework push-pull tubes, P/N 2344790, into P/N 2357984-2 by cutting off swaged end of tube 1/8 inch so that new tube length is 10 inches. Insert large end of plug, P/N 2357980, into tube 1 3/4 inches, drill two 0.161 diameter holes (No. 20 drill) and attach plug to tube with two rivets, P/N AN 430 AD5-16. Machine hex end on socket, P/N 2331924, and install in end of the tube opposite to plug, P/N 2357980. Rework end assemblies, P/N 2331925 into end assemblies, P/N 2357983, and install with locknuts, P/N AN 316-5R and washer 1357982.

Reassemble trim tab mechanism and install on aircraft.

(Douglas Service Bulletin DC-6 No. 123 covers this same subject.)


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