AD 90-19-13

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AD Number:
90-19-13
Document Type:
AD Final Rules
Docket Number:
90-NM-169-AD
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-8F, -61F, -62F, -63F, -71F, -72F, and -73F Series Airplanes
Subject:
Cargo Door Latch Bolts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/01/1990
Make:
The Boeing Company
Model:
DC-8-61F | DC-8-62F | DC-8-63F | DC-8-71F | DC-8-72F | DC-8-73F | DC-8F-54 | DC-8F-55
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Superseded AD: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Superseded By: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: 90-19-13
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-NM-169-AD

AMENDMENT:   39-6734

AD NUMBER:   90-19-13

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-8F, -61F, -62F, -63F, -71F, -72F, and -73F Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective October 1, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
90-19-13 MCDONNELL DOUGLAS: Amendment 39-6734. Docket No. 90-NM-169-AD.

Applicability: All McDonnell Douglas Model DC-8F, -61F, -62F, -63F, -71F, -72F, and -73F series airplanes, certificated in any category.

Compliance: Required as indicated.

To prevent inadvertent opening of the main cargo door in flight, a condition which could result in loss of pressurization and control of the aircraft, accomplish the following:

A. Except as provided in paragraph B. of this AD, within 14 calendar days after the effective date of this AD, unless previously accomplished within the last 30 days, remove sealant in accordance with Figure 1, Step 2, and perform the torque test on the cargo door latch spool fitting attach bolts, in accordance with the Accomplishment Instructions for Group 1, Phase 1, of McDonnell Douglas DC-8 Service Bulletin 52-82, Revision 2, dated January 22, 1990.

NOTE: The requirements of this AD are applicable to all Model DC-8F series airplanes, regardless of effectivity as specified in the McDonnell Douglas Service Bulletin.

1. If a bolt breaks, prior to further flight, replace it with a new bolt and seal in accordance with Figure 1 of the Service Bulletin.

2. If a bolt passes the torque test, prior to further flight, retorque the bolt and seal in accordance with the Accomplishment Instructions for Group 1, Phase 1, of the Service Bulletin.

B. The test required by paragraph A. of this AD is not required for Inconel bolts, part numbers RA21026-7-23, 77711-7-24, and 3D0031-7-24.

C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base for the accomplishment of the requirements of this AD.

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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.

NOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO.

All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, P. O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications, C1-HDR (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California.

This amendment (39-6734, AD 90-19-13) becomes effective on October 1, 1990.


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