AD 89-07-02

AD Final Rules - DRS_89-07-02.html
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AD Number:
89-07-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; McDONNELL DOUGLAS DC-8 Series Airplanes
Subject:
Rudder Drive Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/26/1989
Make:
The Boeing Company
Model:
DC-8-11 | DC-8-12 | DC-8-21 | DC-8-31 | DC-8-32 | DC-8-33 | DC-8-41 | DC-8-42 | DC-8-43 | DC-8-51 | ...Show more
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Superseded AD: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Superseded By: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: 89-07-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6158

AD NUMBER:   89-07-02

SUBJECT HEADING:   Airworthiness Directives; McDONNELL DOUGLAS DC-8 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 26, 1989.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
89-07-02 McDONNELL DOUGLAS: Amendment 39-6158.

Applicability: McDonnell Douglas Model DC-8 series airplanes, equipped with rudder drive torque tube crank assembly, P/N 5647102-1 or -501, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent the loss of directional control of the airplane in critical flight regimes due to fatigue failure of the rudder drive torque tube crank assembly, accomplish the following:

A. Within the next 1,000 hours time-in-service after the effective date of this AD, unless already accomplished within the last 2,600 hours time-in-service, conduct an eddy current inspection of the rudder drive torque tube crank assembly, in accordance with the accomplishment instructions in McDonnell Douglas DC-8 Service Bulletin 27-268, dated February 9, 1988, or equivalent inspection technique approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

B. If no cracks are found, repeat the inspection in accordance with paragraph A. of this AD at intervals not to exceed 3,600 hours time-in-service.

C. If cracks are found, accomplish one of the following:

1. Replace the cracked rudder drive crank assembly (P/N 5647102-1 or -501) with P/N 5647102-501, in accordance with McDonnell Douglas DC-8 Service Bulletin 27-268, dated February 9, 1988, and repeat inspections in accordance with paragraph B. of this AD; or

2. Replace the rudder drive crank assembly with P/N 5647102-503 in accordance with McDonnell Douglas DC-8 Service Bulletin 27-268, dated February 9, 1988.

D. Replacement of the rudder drive crank assembly with P/N 5647102-503, in accordance with McDonnell Douglas DC-8 Service Bulletin 27-268, dated February 9, 1988, constitutes terminating action for the repetitive inspections required by this AD.

E. 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, 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

F. 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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California.

This amendment (39-6158, AD 89-07-02) becomes effective April 26, 1989.


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