AD 88-24-01

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AD Number:
88-24-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BOEING Model 727 Series Airplanes
Subject:
Main Landing Gear Support Link
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/16/1988
Make:
The Boeing Company
Model:
727-100 Series | 727-100C Series | 727-200 Series | 727-200F 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Superseded AD: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Superseded By: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: 88-24-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6057

AD NUMBER:   88-24-01

SUBJECT HEADING:   Airworthiness Directives; BOEING Model 727 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 16, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
88-24-01 BOEING: Amendment 39-6057. Applies to all Model 727 series airplanes, listed in Boeing Service Bulletin 727-32-306, Revision 1, dated February 25, 1988, certificated in any category. Compliance required as indicated, unless previously accomplished.

To prevent failure of the main landing gear support link shaft, which could result in damage to the wing and/or hydraulic system, accomplish the following:

A. Within the next 1,000 hours time-in-service since the last inspection in accordance with AD 68-17-01, and thereafter at intervals not to exceed 1,000 hours time-in-service until the requirements of paragraph B., below, are accomplished, perform an ultrasonic inspection for cracks of the P/N 65- 19657-4, -5, -8, or -13 main landing gear (MLG) support link in accordance with paragraph II, Accomplishment Instructions, Part I - Inspection Data, B. Ultrasonic Inspection Data of Boeing Service Bulletin 32-90, Revision 1, dated May 29, 1968, or Boeing Service Bulletin 32-189, dated May 25, 1971. If any cracks are detected, prior to further flight, perform visual and magnetic particle inspections of the MLG support link shaft as described in paragraph B., below, and replace or modify the MLG support link and bushing accordingly.

B. Except for airplanes identified in paragraph C., below, within the next 6,000 hours time- in-service or 2 years after the effective date of this AD, whichever occurs sooner, perform a visual inspection of the MLG support link shaft for corrosion, and a magnetic particle inspection for cracks. If any corrosion, and/or cracks are detected in the MLG support link shaft, prior to further flight, repair or replace in accordance with Section 32-01-02 of the Boeing 727 Landing Gear Overhaul Manual. In addition, replace or modify the MLG support link, P/N 65-19657-4, -5, -8, -11, -13, -15, -16, or -18, and associated bushing, as necessary, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727-32-306, Revision 1, dated February 25, 1988.

C. In lieu of the requirements of paragraph B., above, for airplanes line numbers 1793 and subsequent, and airplanes that have been modified in accordance with Boeing Service Bulletin 727-32- 306, dated March 26, 1982, and which have had the MLG support links lubricated at intervals not to exceed 500 hours time-in-service: Within the next 6,000 hours time-in-service or 2 years after the effective date of this AD, whichever occurs sooner, or 5 years since the modification, whichever occurs later, perform a visual inspection for corrosion and a magnetic particle inspection for cracks of the MLG support link shaft. If any corrosion and/or cracks are detected in the MLG support link shaft, prior to further flight, repair or replace in accordance with Section 32-01-02 of the Boeing Model 727 Landing Gear Overhaul Manual. In addition, replace or modify the MLG support link and associated bushing, as necessary, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727-32-306, Revision 1, dated February 25, 1988.

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 68-17-01, Amendment 39-635, as amended by Amendment 39-1228.
This amendment, 39-6057, becomes effective December 16, 1988.

FOOTER: