AD 85-21-01

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AD Number:
85-21-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 737-300 Series Airplanes
Subject:
Forward Engine Mount
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/21/1985
Make:
The Boeing Company
Model:
737-300 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Superseded AD: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Superseded By: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: 85-21-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5148

AD NUMBER:   85-21-01

SUBJECT HEADING:   BOEING Model 737-300 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective October 21, 1985.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
85-21-01 BOEING: Amendment 39-5148. Applies to all Model 737-300 series airplanes delivered prior to line position 1147, certificated in any category. Line position 1147 was delivered September 13, 1985. To detect loose cone bolts and interference between the engine and engine support strut at the forward engine mount, accomplish the following within 30 days after the effective date of this AD, unless already accomplished:

A. Visually inspect for clearances between the engine and engine support strut in the vicinity of the forward engine mount as specified in Boeing Telegraphic Service Letter M- 7272-2396, dated September 12, 1985.

B. If the required clearance cannot be confirmed at any location specified in Boeing Telegraphic Service Letter M-7272-2396, dated September 12, 1985, lower the engine in accordance with Boeing Maintenance Manual Section 71-00-02, revised June 25, 1985, sufficiently to accomplish the following:

1. Disassemble as required to inspect the forward cone bolts and forward mount cone bolt receptacles for pitting, galling, or wear and clearances in accordance with Boeing Maintenance Manual Section 71-21-00, revised October 25, 1984.

2. Penetrant-inspect the cone bolt threads as specified in Boeing Telegraphic Service Letter M-7272-2396, dated September 12, 1985.

3. Repair or replace any damaged cone bolts or cone bolt receptacles.

C. Eliminate interference detected in paragraph A., above, in accordance with procedures specified in Boeing Telegraphic Service Letter M-7272-2396, dated September 12, 1985.

D. Following accomplishment of the above, reinstall the engine in accordance with instructions provided in Maintenance Manual Section 71-00-02, revised June 25, 1985, except that the cone bolts must be tightened to 1200-1400 inch-pounds of torque.

E. 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.

F. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.

All persons affected by this AD who have not already received copies of the service information cited herein may obtain copies upon request from the Boeing Commercial Airplane Company, 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 the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.

This amendment becomes effective October 21, 1985.

FOOTER: