AD 75-03-01

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AD Number:
75-03-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 707-300, -300B, - 300C, and -400 Series Airplanes
Subject:
Upper Wing Skin Splice Plate
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/17/1980
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Superseded AD: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Superseded By: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: 75-03-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3737

AD NUMBER:   75-03-01

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

ACTION:  

SUMMARY:  

DATES:   Effective April 17, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
75-03-01 BOEING: Amendment 39-2074 as amended by Amendment 39-2421 and 39-3502 is further amended by Amendment 39-3737. Applies to all Boeing Model 707-300, -300B, - 300C, and -400 series airplanes listed in Boeing Service Bulletin No. 3157, Revision 4, or later FAA approved revisions upon the accumulation of the following number of landings since new:

Models
707-300, -400 13,000 or more landings
707-300B 8,000 or more landings
707-300C 8,000 or more landings

Compliance required as indicated.
To detect cracks in the upper wing skin splice plate at W.S. 360, accomplish the following:
A. Within the next 50 landings, unless accomplished within the last 350 landings, and at intervals thereafter not to exceed 400 landings, inspect the upper wing splice plate at station 360 in accordance with (1), (2), or (3) below. Special attention should be focused in the area of stringer 11 as it is in the high stressed area of the splice plate. If cracks are found, repair prior to further flight in accordance with paragraph B below.
(1) X-Ray inspect per Boeing Service Bulletin No. 3157, Revision 3 and visually inspect the splice plate by removing the aerodynamic sealant between the wing skins from front to rear spar. This inspection method is acceptable for only two successive inspections after the effective date of this amendment.
(2) Low frequency eddy current inspect as specified in Boeing Service Bulletin No. 3157, Revision 7, or inspections approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.
(3) Inspect in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.
B. If cracks are found, repair prior to further flight in accordance with Boeing Service Bulletin No. 2510, Revision 3, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. The repetitive inspections of paragraph A. must be accomplished in areas not covered by repairs per Part VII of Boeing Service Bulletin No. 2510, Revision 3, or later FAA approved revisions.
C. The inspections required by this AD may be terminated when the following is accomplished:
(1) Splice plate, skin and rib cap fastener holes are oversized to remove fatigue material per Part IV of Boeing Service Bulletin No. 2510, Revision 3, or later FAA approved revisions, and complete external doublers are installed in accordance with Part VIII of Boeing Service Bulletin No. 2510, Revision 3, or later FAA approved revisions, or
(2) Other modifications are made in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.
D. For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type.
E. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest 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 change for that operator.
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. The documents may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington.
This supersedes Amendment 39-1829 (39 F.R. 15027), AD 74-09-07, as amended by Amendment 39-2002.
Amendment 39-2074 became effective January 27, 1975.
Amendment 39-3421 became effective December 4, 1975.
Amendment 39-3502 became effective July 3, 1979.
This Amendment 39-3737 becomes effective April 17, 1980.

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