AD 88-25-03

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AD Number:
88-25-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BOEING Model 707-300, -300B, -300C and -400 Series Airplanes
Subject:
Horizontal Stabilizers
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/30/1988
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Superseded AD: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Superseded By: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: 88-25-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6072

AD NUMBER:   88-25-03

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

ACTION:  

SUMMARY:  

DATES:   Effective December 30, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
88-25-03 BOEING: Amendment 39-6072. Applies to all Model 707-300, -300B, -300C, and -400 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished.

NOTE: The inspections required by AD 85-12-01 are not changed by this action.

To prevent the separation of the horizontal stabilizer, accomplish the following:

A. For airplanes on which the modification required by AD 79-01-06 has not been accomplished: Prior to the accumulation of 8,000 total landings, install structural improvement kits on the horizontal stabilizer outer panels and center section in accordance with Boeing Alert Service Bulletin A3313, Revision 9, dated February 25, 1988, Boeing Service Bulletin 3253, Revision 3, dated February 25, 1988, and Boeing Service Bulletin 3331, Revision 3, dated June 15, 1979.

B. For airplanes which have been modified in accordance with Boeing Service Bulletin A3313, Revision 8, or earlier revisions, or Boeing Service Bulletin 3253, Revision 2, or earlier revisions, in compliance with AD 79-01-06: Within one year after the effective date of this AD, rework the clevis fittings in accordance with Boeing Alert Service Bulletin A3313, Revision 9, dated February 25, 1988, and Boeing Service Bulletin 3253, Revision 3, dated February 25, 1988.

C. Accomplishment of the modification requirements of this AD, constitutes terminating action for this AD and AD's 77-16-11 and 78-01-04.

D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office.

E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington.

This amendment supersedes AD 79-01-06, Amendment 39-3388, effective February 10, 1979.
This amendment, 39-6072, becomes effective December 30, 1988.

FOOTER: