AD 88-10-07

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AD Number:
88-10-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes
Subject:
Flap Drive Link Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/25/1988
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Superseded AD: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Superseded By: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: 88-10-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5912

AD NUMBER:   88-10-07

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

ACTION:  

SUMMARY:  

DATES:   Effective May 25, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
88-10-07 MCDONNELL DOUGLAS: Amendment 39-5912. Applies to McDonnell Douglas Model DC-8 series airplanes, equipped with P/N(s) 5644642 or 5751152, LH and RH wing flap drive link assembly installed at wing station XW=97.906, certificated in any category. Compliance required as indicated.

To prevent the loss of airplane control in a critical flight regime due to metal fatigue failure of the flap drive link assembly, accomplish the following:

A. Prior to the accumulation of 6,250 landings on the inboard flap drive link assembly, P/N 5644642 or 5751152, or within the next 375 landings after the effective date of this AD, whichever occurs later, unless already accomplished within the last 375 landings, conduct inspections for fatigue cracking of specific areas of the link assembly in accordance with Figure 2. of McDonnell Douglas DC-8 Alert Service Bulletin A27-269, dated March 25, 1988 (hereafter referred to as SB A27-269).

B. If no cracks are found, repeat inspections in accordance with Figure 2. of SB A27-269, at intervals not to exceed 750 landings.

C. If cracks are found, accomplish the following before further flight:

1. If cracks are within the blend limits of Figure 3. of SB A27-269, rework in accordance with Figure 3. of SB A27-269 and repeat inspections in accordance with Figure 2. of SB A27-269, prior to the accumulation of 750 landings and at intervals thereafter not to exceed 300 landings.

2. If cracks exceed the blend limits of Figure 3. of SB A27-269, replace with new part of the same part number, in accordance with Figure 4. of SB A27-269.

D. 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.

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.

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, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60). This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.

This Amendment becomes effective May 25, 1988.


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