AD 65-21-03

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AD Number:
65-21-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS DC-8 Airplanes
Subject:
Main Landing Gear Strut Pistons
Status:
Current
Citation:
(Federal Register: September 4, 1965)
Citation Publish Date:
09/04/1965
Effective Date:
10/04/1965
Make:
The Boeing Company
Model:
DC-8-11 | DC-8-12 | DC-8-21 | DC-8-31 | DC-8-32 | DC-8-33 | DC-8-41 | DC-8-42 | DC-8-43 | DC-8-51 | ...Show more
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Superseded AD: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Superseded By: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: 65-21-03
CITATION:   [Federal Register: September 4, 1965]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-133

AD NUMBER:   65-21-03

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS DC-8 Airplanes


ACTION:  

SUMMARY:  

DATES:   Effective October 4, 1965.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
65-21-03 DOUGLAS: Amdt. 39-133 Part 39 Federal Register September 4, 1965. Applies to Model DC-8 Airplanes.

Compliance required as indicated.

To prevent further failures of the main landing gear strut piston due to cracking in the radius of the torque link lug, accomplish the following on landing gear strut piston assemblies, Douglas P/N's 5598229, 5598343, 5719155, 5773028, 5773029, and 5773030:

(a) Unless already accomplished, rework assemblies having 4,000 or more hours' time in service on the effective date of this AD -

(1) In accordance with paragraph 2B of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 4,500 hours' time in service after the effective date of this AD; or

(2) In accordance with Douglas TWX MISC-108/DJW dated January 28, 1963, within 500 hours' time in service after the effective date of this AD and in accordance with paragraph 2A of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 4,500 hours' time in service after the effective date of this AD.

(b) Unless already accomplished, rework assemblies having less than 4,000 hours' time in service on the effective date of this AD -

(1) In accordance with paragraph 2B of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before the accumulation of 8,500 hours' time in service; or

(2) In accordance with Douglas TWX MIS-108/DJW dated January 28, 1963, before the accumulation of 4,500 hours' time in service and in accordance with paragraph 2A of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before the accumulation of 8,500 hours' time in service.

(c) Inspect assemblies with 4,000 or more hours' time in service on the effective date of this AD that have not been reworked in accordance with Douglas TWX MISC-108/DJW dated January 28, 1963, in the area of the radius between the main landing gear strut piston torque link lugs for cracks using a dye penetrant inspection method or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 500 hours' time in service after the effective date of this AD unless already accomplished within the last 500 hours' time in service and thereafter at intervals not to exceed 1,000 hours' time in service from the last inspection.

(d) Inspect assemblies with less than 4,000 hours' time in service on the effective date of this AD that have not been reworked in accordance with Douglas TWX MISC-108/DJW in the area of the radius between the main landing gear strut piston torque link lugs for cracks using a dye penetrant inspection method or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before the accumulation of 4,500 hours' time in service unless already accomplished within the last 500 hours' time in service and thereafter at intervals not to exceed 1,000 hours' time in service from the last inspection.

(e) Replace any part having a crack 0.040 inch or more in depth with an undamaged part before further flight. Replace any part having a crack less than 0.040 inch in depth with an undamaged part before further flight or rework it in accordance with paragraph 2B of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before further flight.

(f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.

This directive effective October 4, 1965.


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