AD 88-11-10 R1

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AD Number:
88-11-10 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; AIRBUS INDUSTRIE Model A300 Series Airplanes
Subject:
Engine Cowl Door Latches
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/06/1988
Make:
Airbus
Model:
A300 B2-1A | A300 B2-1C | A300 B2-203 | A300 B2K-3C | A300 B4-103 | A300 B4-203 | A300 B4-2C
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Superseded AD: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Superseded By: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: 88-11-10 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6005

AD NUMBER:   88-11-10 R1

SUBJECT HEADING:   Airworthiness Directives; AIRBUS INDUSTRIE Model A300 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 6, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
88-11-10 R1 AIRBUS INDUSTRIE: Amendment 39-5931 as amended by Amendment 39- 6005. Applies to Model A300 series airplanes, equipped with General Electric CF6-50 engines, without a secondary latching system on core cowl doors, certificated in any category.

Compliance required as indicated, unless previously accomplished.

To prevent structural damage to the airplane due to engine core cowl door separation, accomplish the following:

A. Within 10 days after the effective date of this AD, check the core cowl door latches of each engine once each day, and re-check after each core cowl door is opened and subsequently closed.

1. If the latch is open, before further flight, properly close the latch.

2. If the latch will not engage, adjust the latch, in accordance with the A300 maintenance manual.

3. If the latch cannot be properly adjusted, replace the latch prior to further flight.

B. The checks required by paragraph A., above, may be discontinued after a secondary latching system is installed, in accordance with Airbus Industrie Service Bulletin A300- 71-053, Revision 2, dated January 6,1987.

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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113.

D. 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 the modification required by this AD.

All persons affected by this directive who have not already received the appropriate service information from the manufacturer, may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.

This AD revises AD 88-11-10, Amendment 39-5931.

This amendment, 39-6005, becomes effective September 6, 1988.

FOOTER: