AD 50-40-01

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AD Number:
50-40-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 377 Aircraft
Subject:
Nose Gear Spindle
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
Aero Spacelines, Incorporated
Model:
377 | 377MG | 377SGT
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Superseded AD: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Superseded By: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: 50-40-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   50-40-01

SUBJECT HEADING:   BOEING Model 377 Aircraft

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   50-40-01 BOEING: Applies to all Model 377 Aircraft.
A. Compliance required not later than December 15, 1950, unless already accomplished, and at the periodic inspections nearest a 700-hour interval thereafter if not reinforced as indicated below.
Thoroughly inspect the nose gear spindle for circumferential cracks in the area adjacent to the weld between the nose gear spindle shaft, P/N 9-13735, and the spindle bearing, P/N 6- 25978. Since these cracks are extremely fine, a close magnaflux, dye penetrant or equivalent inspection is required. (Etching process is not recommended.)
If cracks are found, either of the following steps should be taken:
(1) Remove the cracks with 3/8-inch diameter grinding tool such that not more than 0.08 inch of the spindle shaft and not more than 0.10 inch of the weld is removed.
(Boeing Service Letter No. 94 covers this subject.)
If cracks extend beyond these limits the spindle should be reinforced per item (2) below:
(2) Reinforce the nose gear spindle by machining inside of spindle and inserting a 1/2-inch wall steel tube 25-inches long, P/N 5-39516-3.
(Boeing Service Letter No. 138A covers this same subject.)
B. (P/N 15-22594) Compliance required as indicated.
1. Thoroughly inspect the nose landing gear terminal P/N 15-22594, for cracks in the trapezoidal cutout as soon as practicable, but not later than November 1, 1952, unless already accomplished, and continuing at periodic intervals not to exceed 800 hours thereafter. This cutout is visible by removing the cover plate on the lower end of the strut and turning the nose gear segment. If cracks are found, the strut may be reworked in accordance with item 2 below, and provided cracks are removed, strut may be returned to service.
2. If not already accomplished, at the next landing gear overhaul, grind the sides of the trapezoidal cutout to a 0.50 inch radius at corners to conform to the sketch shown in Boeing's Service Letter 148A. The inspection of item 1 above must also be continued after rework until service experience shows that further cracking will not occur.



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