AD 78-01-04

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AD Number:
78-01-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 707-300/400/300B/300C Series Airplanes
Subject:
Horizontal Stabilizer
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/01/1978
Make:
The Boeing Company
Model:
707-300 Series | 707-300B Series | 707-300C Series | 707-400 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Superseded AD: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Superseded By: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: 78-01-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3132

AD NUMBER:   78-01-04

SUBJECT HEADING:   BOEING Model 707-300/400/300B/300C Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 1, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
78-01-04 BOEING: Amendment 39-3112 as amended by Amendment 39-3132. Applies to all Boeing 707-300/400/300B/300C series airplanes upon the accumulation of, or with more than 8,000 landings.
Visually inspect the horizontal stabilizer center section rear spar upper chord for cracks between terminal fittings in accordance with Boeing Service Bulletin 3331 or with the method specified in paragraph B at the time interval specified in paragraph A below. Chords found cracked are to be reworked in accordance with one of the methods noted in paragraph C or replaced with a chord of the same part number prior to further flight.
A. Inspect within the next 375 landings after the effective date of this AD and thereafter at intervals not to exceed 375 landings. Report all cracks found during the initial inspection to the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, noting airplane identification, hours time in service, crack locations and magnitude.
B. Inspection may be accomplished by gaining access to the upper rear surface of the center section and examining the exposed surfaces of the upper chord using a bright light and a mirror at the aft upper and lower surfaces of the chord. If indications of a crack are found, eddy-current or penetrant inspection should be used to confirm presence of crack.
C. Rework in accordance with one of the following:
1. An FAA approved repair provided by the Boeing Company.
2. A method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.
D. With permission of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, the airplane may be flown in accordance with FAR 21.197 to a base where the inspection or repair can be accomplished.
The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1).
All persons affected by this directive who have not already received these documents from the manufacturer, 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 Region, 9010 East Marginal Way South, Seattle, Washington 98108.

Amendment 39-3112 became effective January 15, 1978.
This Amendment 39-3132 becomes effective March 1, 1978.

FOOTER: