AD 84-05-02

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AD Number:
84-05-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 767-200 Series Airplanes
Subject:
Upper Support Fittings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/30/1984
Make:
The Boeing Company
Model:
767-200 Series
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Superseded AD: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Superseded By: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: 84-05-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4827

AD NUMBER:   84-05-02

SUBJECT HEADING:   BOEING Model 767-200 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 30, 1984.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
84-05-02 BOEING: Amendment 39-4827. Applies to Model 767-200 series airplanes, certificated in all categories, listed in Boeing Service Bulletin No. 767-53-2, dated August 19, 1983, or later FAA approved revisions. Compliance required as indicated in the body of the AD.

To ensure the structural integrity of the horizontal stabilizer pivot hinge fitting and adjacent structure accomplish the following, unless already accomplished:

A. Prior to the accumulation of 3000 landings, and thereafter at intervals not to exceed 300 landings, perform the following inspections:

1. Penetrant inspect the upper support fittings for cracks, and check the bolts common to the pivot hinge fitting and the BS 1809.5 bulkhead intercostal fitting for breakage in accordance with Boeing Service Bulletin 767-53-2 dated August 19, 1983, or later FAA approved revisions.

2. Visually inspect the surrounding structure for cracks. If cracks are found in the upper support fitting and not in the surrounding structure, accomplish the modification described in the Service Bulletin before further flight. If cracks are found in the surrounding structure, repair the airplane before further flight, in a manner approved by the Manager, Seattle Aircraft Certification Office.

B. Prior too accumulation of 6000 landings, accomplish the modification described in Boeing Service Bulletin 767-53-2 dated August 19, 1983, or later FAA approved revisions. This action terminates the repetitive inspections required by paragraph A., above.

C. Aircraft may be ferried to a maintenance base for repair in accordance with FAR 21.197 and 21.199.

D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.

E. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, 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 adjustment period.

F. For the purpose of this AD, and when approved by an FAA Maintenance Inspector, the number of landings may be computed by dividing each airplane's time in service by the operator's fleet average time from takeoff to landing for the aircraft type.

All persons affected by this directive who have not already received Boeing Service Bulletin 767-53-2 dated August 19, 1983, may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington.

This amendment becomes effective April 30, 1984.

FOOTER: