AD 89-26-02

AD Final Rules - DRS_89-26-02.html
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AD Number:
89-26-02
Document Type:
AD Final Rules
Docket Number:
89-NM-73-AD
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-9-10 through -80, Model MD88, and C-9 (Military) Seri...Show more
Subject:
Inspect Rudder Control
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/13/1990
Make:
The Boeing Company
Model:
DC-9-11 | DC-9-12 | DC-9-13 | DC-9-14 | DC-9-15 | DC-9-15F | DC-9-21 | DC-9-31 | DC-9-32 | DC-9-32 (...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Superseded AD: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Superseded By: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: 89-26-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   89-NM-73-AD

AMENDMENT:   39-6418

AD NUMBER:   89-26-02

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-9-10 through -80, Model MD88, and C-9 (Military) Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 13, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
89-26-02 MCDONNELL DOUGLAS: Amendment 39-6418. Docket No. 89-NM-73-AD.

Applicability: Model DC-9-10 through -80, Model MD88, and C-9 (Military) series airplanes, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To preclude failure of the rudder control sector, accomplish the following:

A. Within 60 days after the effective date of this airworthiness directive (AD), visually inspect the rudder control sector for cracks and acceptable wall thickness, in accordance with Figure 2 of McDonnell Douglas Alert Service Bulletin A27-302, dated February 17, 1989.

1. If no cracks are found and the wall thickness is more than .020 inch, no further action is required.

2. If cracks are found or if a wall thickness of .020 inch or less is found, prior to further flight, perform either a permanent or temporary repair or replace the rudder control sector, in accordance with the accomplishment instructions of McDonnell Douglas Service Bulletin A27-302, dated February 17, 1989.

3. If a temporary repair is performed, replace or permanently repair the rudder control sector within 6 months or 1,000 landings, whichever occurs earlier, in accordance with McDonnell Douglas Service Bulletin A27-302, dated February 17, 1989.

B. Within 15 days after the inspection required by paragraph A., above, submit a report of findings, positive or negative, to the Los Angeles Aircraft Certification Office, Attention: ANM-108L, FAA, Northwest Mountain Region, 3229 East Spring Street, Long Beach, California 90806-2425.

C. An alternate means of compliance or adjustment of the compliance times, 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 will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C2-165 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California.

This amendment (39-6418, AD 89-26-02) becomes effective January 13, 1990.


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