AD 89-23-52

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AD Number:
89-23-52
Document Type:
AD Final Rules
Docket Number:
89-NM-231-AD
Subject Heading:
Airworthiness Directives; BOEING Model 737-300 and -400 Series Airplanes
Subject:
Entry Door Bolts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/16/1990
Make:
The Boeing Company
Model:
737-300 Series | 737-400 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Superseded AD: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Superseded By: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: 89-23-52
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   89-NM-231-AD

AMENDMENT:   39-6500

AD NUMBER:   89-23-52

SUBJECT HEADING:   Airworthiness Directives; BOEING Model 737-300 and -400 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 16, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
89-23-52 BOEING: Amendment 39-6500. Final copy of telegraphic AD. Docket No. 89-NM- 231-AD.

Applicability: Model 737-300 and -400 series airplanes, line numbers 1770 to 1783, 1785, and 1787 to 1789, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent the loss of the forward entry door and subsequent rapid decompression of the airplane, accomplish the following:

A. Within 24 hours (clock hours, not flight hours) after the effective date of this amendment, incorporate the following limitation into the Limitations Section of the FAA- approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM.

"Airplane Pressurization
Do not exceed 4.7 psi cabin pressure differential."

B. Within 20 flights after the effective date of this amendment, inspect the forward left entry door, fuselage aft frame, bottom door stop fitting at body station (BS) 349, water line (WL) 216, left buttock line (LBL) 65, for missing bolts (two) attaching the inboard side of the door stop fitting to the fitting support intercostal.

1. If two bolts are found, the AFM limitations required by paragraph A., above, may be removed and no further action is required.

2. If one or both bolts are missing, inspect and repair prior to further flight, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. The AFM limitations required by paragraph A., above, may be removed and no further action is required.

C. Within 10 days after completion of the inspection required by paragraph B., above, for each airplane, submit a report of inspection findings, positive or negative, to the Manager, Seattle Manufacturing Inspection District Office, 7300 Perimeter Road South, Seattle, Washington 98108. This report must include the model of the airplane inspected, the date of inspection, and the number of bolts installed.

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 will either concur or comment, 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.

This amendment (39-6500, AD 89-23-52) becomes effective on February 16, 1990, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T89-23-52, issued November 3, 1989, which contained this amendment.

FOOTER: