AD 69-18-03

AD Final Rules - DRS_69-18-03.html
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AD Number:
69-18-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-8-42, DC-8-43, DC-8F-54, DC-8F-55, DC-8-61, DC-8-62, ...Show more
Subject:
Static Pipe Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/03/1969
Make:
The Boeing Company
Model:
DC-8-42 | DC-8-43 | DC-8-61 | DC-8-62 | DC-8-62F | DC-8-63 | DC-8-63F | 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Superseded AD: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Superseded By: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: 69-18-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-832

AD NUMBER:   69-18-03

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-8-42, DC-8-43, DC-8F-54, DC-8F-55, DC-8-61, DC-8-62, DC-8-62F, DC-8-63 and DC-8-63F Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective September 3, 1969.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
69-18-03 MCDONNELL DOUGLAS: Amdt. 39-832. Applies to McDonnell Douglas Models DC-8-42, DC-8-43, DC-8F-54, DC-8F-55, DC-8-61, DC-8-62, DC-8-62F, DC-8-63 and DC-8-63F aircraft listed in McDonnell Douglas Service Bulletin No. 34-107, revised August 20, 1969, or later FAA approved revision.

Compliance required within the next 200 hours' time in service after the effective date of this AD, unless already accomplished.

To detect possible chafing on the static pipe assembly by the aircraft control cables due to improper clearance from the static pipe assembly, accomplish the following, or an equivalent inspection or modification approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(a) Inspect the first officer's static system for proper clearance, minimum 1/2 inch, between the static pipe assembly, P/N 7646168-228 or 7754670-105, and the aircraft control cables and for evidence of possible chafing on the static pipe assembly by the aircraft control cables. The static pipe assembly is located below the floor directly under the electrical power equipment panel in the cockpit area.

(b) (i) If the proper clearance, minimum 1/2 inch, is found and there is no evidence of chafing no further action is necessary.

(ii) If the proper clearance, minimum 1/2 inch, is not found and there is no evidence of chafing, provide the proper clearance, minimum 1/2 inch, in accordance with the Douglas Service Bulletin, No. 34-107, revised August 20, 1969, or a later FAA approved revision, prior to further flight.

(iii) If there is evidence of chafing, replace the static pipe assembly, P/N 7646168-228 or 7754670-105, and provide proper clearance, minimum 1/2 inch, in accordance with the Douglas DC-8 Service Bulletin, No. 34-107, revised August 20, 1969, or a later FAA approved revision, prior to further flight.

(iv) Aircraft upon which repairs must be accomplished may be flown in accordance with FAR 21.197 to a base where the repair can be performed.

NOTE: McDonnell Douglas advises that a Service Bulletin No. 34-108, will be issued in September, 1969, describing the installation of a new static pipe design in place of static pipe assembly, P/N 746168-228 or 7754670-105. Based on present information, the installation will constitute an equivalent modification; and, if accomplished, will be considered as an alternative method of compliance with this AD.

This Amendment becomes effective September 3, 1969.


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