AD 51-01-01

AD Final Rules - DRS_51-01-01.html
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AD Number:
51-01-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS All DC-6 Aircraft
Subject:
Attachment Bolt Replacement
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Superseded AD: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Superseded By: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: 51-01-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   51-01-01

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS All DC-6 Aircraft

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
51-01-01 DOUGLAS: Applies to All DC-6 Aircraft.

To be accomplished as indicated below.

(a) All airplanes at each 300 hours of flight time-Inspect for broken studs at the front spar lower and upper fittings at wing joint Station 421. Also inspect lower forward front spar fittings, P/N 4332884 and -1, and upper forward fittings, P/N 4332885 and -1, for cracks in area approximately 2 inches outboard of fitting face.

(b) If broken stud is found, replace both studs at spar fittings with parts having threads rolled after heat treat, install bolt with threads rolled after heat treat at center spar, and replace lower fitting P/N 4332884 and -1 and upper fitting P/N 4332885 and -1 with newly designed heavier fittings P/N 4397872 and -1 and P/N 4397873 and -1, respectively. Return of an airplane to service prior to the availability of the newly designed fittings is permissible by installation of new fittings of the old design (P/N 4332884 and 4332885), providing replacement is made at or before 8,000 hours of service on those parts. Spotface new fittings after installation to align with adjacent fittings.

If records show previous case of broken parts at front spar fitting, and only corrective action taken was the replacement of studs with threads rolled after heat treat, inspect fittings at each 300 hours of operation until same replacement action outlined above is taken at next engine change period.

(c) Continue inspections outlined in (a), until following replacement action is accomplished:

1. If not previously incorporated, install studs at the front spar and bolts at the center spar which have threads rolled after heat treat. (See AD 49-06-02.)

2. Replace the lower forward front spar fittings P/N 4332884 and -1 with new heavier P/N 4397872 and -1 and replace the upper forward front spar fitting P/N 4332885 and -1 with new heavier P/N 4397873 and -1 spotfacing fittings after installation.

(d) Replacement action outlined in item (c) 1 and 2, to be accomplished not later than January 1, 1952.

(Douglas General Service Letter DC-6 No. 61 covers this same subject. Refer to Douglas Service Letter No. 66, Supplement No. 2 dated July 18, 1951, for wing alignment at Station 421.)


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