AD 86-17-04

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AD Number:
86-17-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 757-200 Series Airplanes
Subject:
Self-Locking Nuts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/05/1986
Make:
The Boeing Company
Model:
757-200 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Superseded AD: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Superseded By: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: 86-17-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5369

AD NUMBER:   86-17-04

SUBJECT HEADING:   BOEING Model 757-200 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 5, 1986.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
86-17-04 BOEING: Amendment 39-5369. Applies to all Model 757-200 series airplanes listed in Boeing Service Letter 757-SL-27-24-B, dated June 2, 1986, certificated in any category.

To detect nuts that have insufficient self-locking torque characteristics, installed on the nose gear door actuator attachment, main landing gear jury brace support attachment, main landing gear forward trunnion drag fitting aft attachment, and the P&W 2037 engine front evener bar attachment, accomplish the following, unless already accomplished:

A. Within the next 90 days after the effective date of this AD, check the Category II self-locking nuts, P/N BACN10JC12CM or BACN10JC12CD, except the rudder pedal adjustment cable retainer self-locking nut, for proper self-locking torque in accordance with Paragraph II of Boeing Service Letter 757-SL-27-24-B, dated June 2, 1986, or later FAA- approved revision. If any self-locking nut is found not to meet the self-locking torque criteria of Boeing Service Letter 757-SL-27-24-B, dated June 2, 1986, or later FAA-approved revision, it must be replaced prior to further flight with a nut which meets the self-locking torque criteria.

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

C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD.

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

This amendment becomes effective September 5, 1986.

FOOTER: