AD 74-08-06

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AD Number:
74-08-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS DC-10, Series 10, 30, and 40 Airplanes
Subject:
Landing Gear System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/03/1974
Make:
The Boeing Company
Model:
DC-10-10 | DC-10-10F | DC-10-30 | DC-10-30F (KC-10A, KDC-10) | DC-10-40
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 74-08-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1855

AD NUMBER:   74-08-06

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS DC-10, Series 10, 30, and 40 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective June 3, 1974.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
74-08-06 DOUGLAS AIRCRAFT: Amendment 39-1810 as amended by Amendment 39-1855. Applies to Model DC-10, Series 10, 30, and 40 airplanes with the factory serial numbers as indicated in Douglas Alert Service Bulletin No. A32-82, dated May 13, 1974, or later FAA-approved revisions.

Compliance required as indicated.

To prevent a failure to actuate of the landing gear alternate freefall system caused by a jamming of the landing gear control valve slide, Part No. AYG7043-1, in the sleeve, Part No. AYG 7039-1, accomplish the following:

(a) Beginning with the effective date of this AD, on each day in which the aircraft is used, and after any use of the alternate gear extension handle, check the bypass control crank for freedom of movement. The landing gear control valve, Part No. AYG7050, is located in the right hand wheel well, forward center panel of the keel webb. The bypass control crank is next to the keel webb on the forward lower end of the valve. Freedom of movement of the bypass valve is verified by manually moving the crank up and down. If the crank cannot be moved freely by hand, free the crank by exerting a downward force. The downward force exerted must not be excessive. If the crank freedom of movement is not achieved, replace the landing gear control valve, Part No. AYG7050, prior to further flight. Continue these checks for crank freedom of movement until a stop is installed on the landing gear control valve in accordance with Douglas Alert Service Bulletin No. A32-76, Revision 1, dated March 1, 1974, and Douglas Alert Service Bulletin No. A32-82, dated May 13, 1974, or later FAA-approved revisions. Incorporation of both service bulletins is required.

(b) Within the next 1500 hours in service after the effective date of this AD, unless previously accomplished, install a stop on the landing gear control valve, Part No. AYG7050, in accordance with Douglas Alert Service Bulletin No. A32-76, Revision 1, dated March 1, 1974, and Douglas Alert Service Bulletin No. A32-82, dated May 13, 1974, or later FAA-approved revisions. Incorporation of both service bulletins is required. This installation of an external stop on the valve housing will prevent the lever moving to a point that would allow internal jamming.

(c) Within 24 hours after the effective date of this AD unless previously accomplished, conduct an inspection of the landing gear control valve stop clearance as prescribed in Phase I of Douglas Alert Service Bulletin No. A32-82, dated May 13, 1974, or later FAA-approved revisions if the landing gear control valve stop has been installed as required by paragraph (b) of this AD. If the clearance is .050 inch or less, Phase II of the Douglas Alert Service Bulletin No. A32-82 must be accomplished prior to next flight.

(d) The Chief, Aircraft Engineering Division, FAA Western Region, may approve equivalent inspection procedures or modifications.

(e) Aircraft may be operated to a base for accomplishment of the maintenance required by this AD per FAR's 21.197 and 21.199.

Amendment 39-1810 became effective April 8, 1974.

This amendment 39-1855 becomes effective June 3, 1974.


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