AD 79-19-01 R2

AD Final Rules - DRS_79-19-01_R.html
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AD Number:
79-19-01 R2
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 720/720B, 707-300, 707-400, 707- 300B, and 707-300C Series Airplanes
Subject:
Splice Stringers Inspection
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/15/1982
Make:
The Boeing Company
Model:
707-300 Series | 707-300B Series | 707-300C Series | 707-400 Series | 720 Series | 720B 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Superseded AD: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Superseded By: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: 79-19-01 R2
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4486

AD NUMBER:   79-19-01 R2

SUBJECT HEADING:   BOEING Model 720/720B, 707-300, 707-400, 707- 300B, and 707-300C Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 15, 1982.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
79-19-01 R2 BOEING: Amendment 39-3556 as amended by Amendment 39-4087 is further amended by Amendment 39-4486. Applies to all Boeing 720/720B, 707-300, 707-400, 707- 300B, and 707-300C series airplanes.
A. After the effective date of this amendment, perform a low frequency eddy current inspection for cracks in the wing lower surface splice stringers in accordance with Boeing Service Bulletin 3226, Rev. 5, dated November 15, 1981, or later FAA approved revisions, or in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. Inspections are to be made at the threshold times, within the prescribed initial interval and at repetitive intervals shown below:
At the inboard nacelle strut drag brace, the affected lower skin area covered by the fairing may be visually inspected for cracks and evidence of fuel leakage. If crack indications are noted in stringers, or skin cracks or fuel leakage are found at the diagonal brace fairing area, tank entry and inspection by high frequency eddy current of the wing splice stringers is required.

Airplane	Threshold	Initial Inspection within		Repetitive Interval
			unless accomplished
within the last	
720/720B	14,000 ldgs	715 ldgs	715 ldgs	1,430 ldgs
707-300/400	21,000 ldgs	1,675 ldgs	1,675 ldgs	3,350 ldgs
707-300B	19,000 ldgs	1,425 ldgs	1,425 ldgs	2,850 ldgs
707-300C	17,000 ldgs	725 ldgs	725 ldgs	1,450 ldgs
707-300C
	17,000 ldgs	1,425 ldgs	1,425 ldgs	2,850 ldgs

(passenger only)				

B. If cracks are found, repair prior to further revenue flight in accordance with a method approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.
C. For the purpose of complying with this AD and subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's time-in-service by the operator's fleet average from takeoff to landing for the airplane type.
D. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region may adjust the inspection interval if the request contains substantiating data to justify the increase for that operator.
E. Airplanes with cracked splice stringers may be flown in accordance with FAR 21.197 to a base where repairs can be performed.
All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at the FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington.

Amendment 39-3556 became effective September 18, 1979.
Amendment 39-4087 became effective May 17, 1981.
This Amendment 39-4486 becomes effective November 15, 1982.

FOOTER: