AD 89-08-12 R1

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AD Number:
89-08-12 R1
Document Type:
AD Final Rules
Docket Number:
89-NM-128-AD
Subject Heading:
Airworthiness Directives; BOEING Model 737-200, -300, and -400 Series Airplanes
Subject:
Fire/Overheat Detection Module
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/12/1990
Make:
The Boeing Company
Model:
737-200 Series | 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Superseded AD: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Superseded By: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: 89-08-12 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   89-NM-128-AD

AMENDMENT:   39-6462

AD NUMBER:   89-08-12 R1

SUBJECT HEADING:   Airworthiness Directives; BOEING Model 737-200, -300, and -400 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 12, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
89-08-12 R1 BOEING: Amendment 39-6187 as revised by Amendment 39-6462. Docket No. 89-NM-128-AD.

Applicability: Model 737-200, -300, and -400 series airplanes, as listed in Boeing Service Bulletin 737-26-1063, dated May 18, 1989, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To reduce the potential for dispatching an airplane with an inoperative fire/overheat system, accomplish the following:

A. Within 10 days after April 24, 1989 (effective date of Amendment 39-6187), inspect the engine fire/overheat detection module to determine the part number.

1. If part number 10-61096-41, -71, -81, -91, -92, or 10-62061-1, -2, -3, - 11, or -12 is installed, add the following Engine Fire Detection System Test Procedure to 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:

a. Prior to engine start, accomplish fire/overheat warning system test.

b. After engine start, and with the electrical power supply system in the flight configuration, accomplish the fire/overheat warning system test.

c. In the event of an electrical power supply configuration change in flight (e.g., generator failure), perform the fire/overheat warning system test. In the event that this test is unsuccessful, land at the nearest suitable airport.

2. If part numbers other than those listed in paragraph A.1., above, are installed, no further action is required.

B. Within 120 days after the effective date of this amendment, modify the engine fire/overheat detection module, in accordance with Boeing Service Bulletin 737-26-1063 dated May 18, 1989. Once this modification is accomplished, the limitation required by paragraph A.1., above, may be removed from the AFM.

C. 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.

D. 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, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.

This AD revises AD 89-08-12, Amendment 39-6187.
This amendment (39-6462, AD 89-08-12 R1) becomes effective on February 12, 1990.

FOOTER: