AD 80-22-07

AD Final Rules - DRS_80-22-07.html
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AD Number:
80-22-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-6, DC-6A, DC-6B Airplanes including Military Models R...Show more
Subject:
Nose Gear Torque Link
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/03/1980
Make:
The Boeing Company
Model:
DC-6 | DC-6A | DC-6B | Navy R6D-1 | Navy R6D-1Z | USAF C-118A
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Superseded AD: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Superseded By: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: 80-22-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3958

AD NUMBER:   80-22-07

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-6, DC-6A, DC-6B Airplanes including Military Models R6D and C-118

ACTION:  

SUMMARY:  

DATES:   Effective November 3, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-22-07 MCDONNELL DOUGLAS: Amendment 39-3958. Applies to Model DC-6, DC-6A, DC-6B airplanes certificated in all categories including military models R6D and C-118 eligible for civil certification, incorporating nose landing gear upper torque link assembly P/N 8488A-46.

Compliance is required as indicated unless already accomplished.

To prevent failure of the nose landing gear upper torque link which could result in nose gear collapse accomplish the following:

(a) Within 100 hours' time in service from the effective date of this AD unless already accomplished in the last 200 hours' time in service and thereafter at intervals not to exceed 300 hours' time in service since the last such inspection; inspect the nose landing gear upper torque link P/N 8488A-46-1 for cracks at the shoulder recess corner radius, by dye penetrant methods after removing paint per standard shop practice. Do not use a wood (or other) wedge to preload the lugs.

(b) If cracks are found:

(1) The cracked part may be replaced with a like serviceable part of the same part number provided that the replacement part is dye penetrant inspected for cracks within 300 hours' time in service from installation and thereafter at intervals not to exceed 300 hours' additional time in service since the last such inspection, or

(2) The cracked part may be replaced with a like serviceable part of the same part number, reworked as shown on Figures 2 and 3 of Douglas Aircraft Company Service Bulletin No. 641 dated October 18, 1955, and the repetitive inspection requirements of paragraph (a) of this AD are applicable, or

(3) The cracked part may be replaced by like serviceable P/N 8488A-46A-1 of improved design in which case no additional inspections are required by this AD.

(c) If no cracks are found:

(1) Return P/N 8488A-46-1 part to service provided that it is inspected per paragraph (a) of this AD at intervals not to exceed 300 hours' time in service since the last such inspection.

(2) Return P/N 8488A-46-1 part reworked per Figure 5 or Figure 2 of Douglas Aircraft Service Bulletin No. 461 dated October 13, 1955 to service provided that it is inspected per paragraph (a) of this AD at intervals not to exceed 300 hours' time in service since the last such inspection.

(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD.

(e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.

This supersedes AD 54-23-02.

This amendment becomes effective November 3, 1980.


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