AD 62-27-04

AD Final Rules - DRS_62-27-04.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
62-27-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS DC-8
Subject:
Outboard Pylons Spar Cap Structure
Status:
Current
Citation:
(Federal Register: December 20, 1962)
Citation Publish Date:
12/20/1962
Effective Date:
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 ...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Superseded AD: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Superseded By: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: 62-27-04
CITATION:   [Federal Register: December 20, 1962]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   62-27-04

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS DC-8

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
62-27-04 DOUGLAS: Amdt. 520 Part 507 Federal Register December 20, 1962. Applies to DC-8 Standard Leading Edge Aircraft Powered With Pratt & Whitney JT3C, JT4A or Conway Engines.

NOTE: Does not apply to aircraft with extended leading edge and to JT3D powered aircraft with standard leading edge.

Compliance required as indicated.

As a result of failure of the upper inboard spar cap structure of the outboard pylons, accomplish the following:

(a) Unless already accomplished within the last 425 hours' time in service, within the next 25 hours' time in service, inspect upper inboard spar cap structure of the outboard pylon for evidence of cracks. Gain access to the area to be inspected by removing the pylon leading edge nose cap between Station YOP 214 and 244 and access doors numbers 110, 113, 411, and 414. Using close visual or dye penetrant methods, inspect the upper inboard cap and adjacent structure for cracks in the area of Station YOP 230 and at the edges of support fitting P/N 3647306-501.

(b) If cracks are found, repair in accordance with Douglas Drawing 5776811 or FAA approved equivalent, prior to further flight.

(c) If no cracks are found the inspections outlined in (a) must be repeated at periods not to exceed 500 hours' time in service from the last inspection.

(d) The repetitive inspections may be discontinued on aircraft repaired in accordance with Douglas Drawing 5776811 and on aircraft modified to incorporate preventive rework accomplished in accordance with FAA engineering approved technical data.

(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, 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.

(Douglas DC-8 Alert Service Bulletin A54-33, Revision No. 2, dated January 24, 1964, covers this same subject.)

This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated November 21, 1962.

Revised June 8, 1963.

Revised June 23, 1964.


FOOTER: