AD 88-17-06

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AD Number:
88-17-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BOEING Model 727 Series Airplanes
Subject:
Wing Surface Stringers
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/05/1988
Make:
The Boeing Company
Model:
727-100 Series | 727-100C Series | 727-200 Series | 727 Series | 727C 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Superseded AD: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Superseded By: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: 88-17-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5988

AD NUMBER:   88-17-06

SUBJECT HEADING:   Airworthiness Directives; BOEING Model 727 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 5, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
88-17-06 BOEING: Amendment 39-5988. Applies to Model 727 series airplanes, except Model 727-200F, certificated in any category.

Compliance required as indicated, unless previously accomplished.

To ensure the structural integrity of the wing upper surface stringers, accomplish the following:

A. Using eddy current, x-ray, or visual inspection techniques, inspect wing upper surface stringers for cracks, in accordance with Boeing Alert Service Bulletin 727-57A159, Revision 1, dated October 29, 1982, as follows:

1. For airplanes with 45,000 or more landings on August 16, 1983, inspect prior to the accumulation of 1,000 additional landings after August 16, 1983.

2. For airplanes with at least 40,000 and less than 45,000 landings on August 16, 1983, inspect prior to the accumulation of 2,000 additional landings after August 16, 1983.

3. For all other airplanes, inspect prior to the accumulation of 3,000 additional landings after August 16, 1983, or prior to accumulating 33,000 total landings, whichever occurs later.

B. Repeat the inspections required by paragraph A., above, and, if applicable, paragraph C., below, at the following intervals:

1. If the immediately preceding inspection was performed using eddy current methods, reinspect within the next 22,000 landings.

2. If the immediately preceding inspection was performed using x-ray or visual methods, reinspect within the next 11,000 landings.

C. If cracks are detected during the inspections required by paragraph A. or B., above, unless previously accomplished, inspect the stringer-to-rib attachment at wing stations (WS) 519.0 and 546.5 for cracks, using eddy current, x-ray, or visual techniques, in accordance with Boeing Alert Service Bulletin 727-57A159, Revision 3, dated September 18, 1986, in accordance with the following schedule:

1. Prior to the accumulation of 4,500 landings after the effective date of this AD, for airplanes on which cracks have been detected prior to the effective date of this AD.

2. Prior to further flight, for airplanes on which cracks have been detected after the effective date of this AD.

D. Any cracked structure detected as a result of the inspections required by paragraphs A., B., C., E., or F. of this AD, must be repaired prior to further flight, in accordance with a procedure listed in Boeing Alert Service Bulletin 727-57A159, Revision 3, dated September 18, 1986. Repair or modification in accordance with Boeing Alert Service Bulletin 727-57A159, Revision 3, dated September 18, 1986, eliminates the repetitive inspection requirements of paragraph B., above, and constitutes terminating action for only those attachments so repaired or modified.

E. Within the next 4,500 landings after the effective date of this AD, unless previously accomplished in accordance with Boeing Service Bulletin 727-57A159, Revision 3, dated September 18, 1986, inspect and modify stringers (excluding stringer tabs) previously repaired utilizing the preventative modification in accordance with Figure 12 of Boeing Service Bulletin 727-57A159, Revision 1, dated October 29, 1982, or Revision 2, dated March 30, 1984.

F. For airplanes with affected wing stringer rib attach locations previously repaired in accordance with Structural Repair Manual Subject 57-10-4 or any other FAA-approved method (except those identified in paragraph E., above), that have accumulated 22,000 landings prior to August 16, 1983, inspect in accordance with paragraph A., above, within the next 11,000 landings after August 16, 1983, or prior to the accumulation of 33,000 landings since repair, whichever occurs later, and thereafter at intervals in accordance with paragraph B. of this AD.

G. 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.

H. 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.

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 98124-2207. 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 83-13-03, Amendment 39-4673.
This amendment, 39-5988, becomes effective September 5, 1988.

FOOTER: