AD 74-05-04

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AD Number:
74-05-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10 Series Airplanes
Subject:
Yaw Computer
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/06/1974
Make:
The Boeing Company
Model:
DC-10-10 | DC-10-10F
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Superseded AD: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Superseded By: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: 74-05-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1793

AD NUMBER:   74-05-04

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 6, 1974.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
74-05-04 MCDONNELL DOUGLAS: Amdt. 39-1793. Applies to all Douglas Aircraft Company DC-10-10 series airplanes.

Compliance required within 300 hours additional time in service after the effective date of this airworthiness directive, unless previously accomplished.

(1) Inspect all DC-10-10 airplanes to determine if a yaw computer Part No. 1954094-6 is installed. Remove the inoperative placard from the yaw damper test function on the overhead test panel, if installed.

(2) If yaw computer Part No. 1954094-6 is installed in either or both positions, install, prior to further flight, the following placards for the yaw damper test function:

(a) "INOP" on each "YAW DAMP TEST FAIL" light.

(b) "SEE AFM FOR TEST PROCEDURE" to the left on the word "TEST" on the overhead yaw damper panel.

(3) Incorporate the following limitation and procedure in the DC-10-10 FAA Approved Airplane Flight Manual for the use of the flight crew. An alternate test procedure may be substituted upon submission of adequate substantiating data to the Chief, Aircraft Engineering Division, FAA Western Region, and the receipt of an approval of the alternate procedure from the Chief.

Incorporate revisions in the FAA Approved Airplane Flight Manual Documents No. MDC J1010 or MDC J1010, Appendix X, as follows:

(a) Revise existing paragraph heading in Section I, Limitations, to read: YAW DAMPER

Any two channels must be operating prior to the start of takeoff. (See yaw damper computer Part No. 1954094-6 test procedure in Section III of FAA Approved Airplane Flight Manual.)

(b) Incorporate the following heading in Section III of FAA Approved Airplane Flight Manual Document No. MDC J1010 or MDC J1010, Appendix X, to read:

TEST PROCEDURE FOR YAW DAMPER COMPUTER PART NO. 1954094-6 INSTALLED IN EITHER OR BOTH POSITIONS

During taxi:

(1) Place all four (upper and lower) yaw damper switches ON.

(2) Center rudder indices in the surface position indicator with the rudder pedals.

(3) When entering a turn, using primary nose wheel steering, observe the surface position indicator and note that the rudder position indices deflect to the first vertical mark opposite to the direction of turn.

-Any rudder surface (position indicator) with only one yaw one yaw damper operative will deflect only one half the rudder deflection noted with two yaw dampers operative.

(4) If this test indicates inoperative yaw damper(s), the yaw damper(s) associated with the failed system (upper or lower) must be switched OFF.

This amendment becomes effective March 6, 1974.


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