AD 57-16-03

AD Final Rules - DRS_57-16-03.html
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AD Number:
57-16-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS All Model DC-7 Series Aircraft
Subject:
Elevator Tab Pushrod
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
The Boeing Company
Model:
DC-7 | DC-7B | DC-7C
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Superseded AD: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Superseded By: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: 57-16-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   57-16-03

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS All Model DC-7 Series Aircraft

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
57-16-03 DOUGLAS: Applies to All Model DC-7 Series Aircraft Prior to Fuselage No. 697.

Compliance required as indicated.

Numerous cases have been reported wherein fatigue failures have occurred in the elevator control tab pushrod assembly, P/N 4499117. Investigation reveals that tubes reamed to accommodate the end fittings are unsatisfactory. Also, it has been determined that P/N 4499117 as well as other assemblies, P/N's 2357984, 3593467, and 4335618, have been reamed to permit installation of the end fittings.

Unless already accomplished, inspect all the above assemblies within the next 300 hours for fatigue cracks or reaming. Unless disassembled x-ray is believed to be the only reliable means of verifying whether the tubes have been reamed in excess of the limits specified by Douglas.

If cracks are found or reaming exceeds the limits specified in Douglas Service Bulletin DC-7 No. 181 reissued February 8, 1957, the part must be replaced.

All parts reamed within tolerances specified in the Douglas Service Bulletin must be visually reinspected for fatigue cracks at intervals not to exceed 300 hours. When P/N's 4335618 and 4499117 as well as any P/N 3593467, which have been reamed, are replaced with P/N 359347 now manufactured by controlling the swaging of the tube instead of reaming to permit installation of the end fittings, the repeated inspection may be discontinued.

(Douglas Service Bulletin DC-7 No. 132 revised November 13, 1956, covers the installation of P/N 3593467 and the associated changes required to make the installation on aircraft originally incorporating P/N 4335618 or P/N 4499117.)

This supersedes AD 56-24-04.


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