AD 87-13-10

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AD Number:
87-13-10
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-9-30, -40, and C-9 (Military) Series Airplanes
Subject:
Rudder Drive Crank Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/08/1987
Make:
The Boeing Company
Model:
DC-9-31 | DC-9-32 | DC-9-32 (VC-9C) | DC-9-32F | DC-9-32F (C-9A) | DC-9-32F (C-9B) | DC-9-33F | DC-9...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Superseded AD: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Superseded By: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: 87-13-10
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5666

AD NUMBER:   87-13-10

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-9-30, -40, and C-9 (Military) Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective August 8, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
87-13-10 MCDONNELL DOUGLAS: Amendment 39-5666. Applies to McDonnell Douglas Model DC-9-30, -40, and C-9 (Military) series airplanes, Fuselage Numbers 1 through 1084, certificated in any category. Compliance required as indicated, unless previously accomplished.

To prevent the failure of the rudder drive crank assembly, accomplish the following:

A. Within 1,000 landings or 150 days after the effective date of this AD, whichever occurs earlier, unless already accomplished within the last 2,000 landings or 7 months, eddy current or ultrasonically inspect the rudder drive crank assembly for cracks in accordance with McDonnell Douglas DC-9 Service Bulletin 27-261, Revision 1, dated April 3, 1987, or later FAA-approved revisions.

1. If no cracks are found, accomplish repetitive inspections at intervals not to exceed 12 months or 3,000 landings, whichever occurs earlier, until such time as the procedures described in paragraph A.3., below, are accomplished.

2. If crack(s) are found, before further flight, replace cracked rudder drive crank assembly with a new P/N 5912801-1 or -501 drive crank. If a new 5912801-1 drive crank assembly is used as a replacement part, inspect in accordance with paragraph A.1., above.

3. Installation of rudder drive crank assembly P/N 5912801-501, in accordance with McDonnell Douglas DC-9 Service Bulletin 27-261, Revision 1, dated April 3, 1987, or later FAA-approved revisions, constitutes terminating action for the repetitive inspections required by paragraph A.1., above.

B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

C. Upon the request of an operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the change for that operator.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 4344 Donald Douglas Drive, Long Beach, California.

This amendment becomes effective August 8, 1987.


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