AD 63-08-02

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AD Number:
63-08-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS DC-8 Series Aircraft
Subject:
Elevator Control Tab Push Rod
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
The Boeing Company
Model:
DC-8-11 | DC-8-12 | DC-8-21 | DC-8-31 | DC-8-32 | DC-8-33 | DC-8-41 | DC-8-42 | DC-8-43 | DC-8-51 | ...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Superseded AD: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Superseded By: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: 63-08-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-630

AD NUMBER:   63-08-02

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS DC-8 Series Aircraft

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
63-08-02 DOUGLAS: Amendment 39-630. McDonnell Douglas. Applies to McDonnell Douglas Model DC-8 Series Aircraft equipped with P/N 3703218 (no dash number) elevator control tab push rod assembly.

As a result of damage near the midpoint of the elevator control tab push rod assembly due to wear from rubbing against the guide support assembly and the guide support attach rivets, accomplish the following:

(a) Unless already accomplished, within the next 300 hours' time in service after the effective date of this AD:

(1) Remove both left and right-hand elevator control tab push rod assemblies, P/N 3703218, and conduct a close visual inspection of the push rods for evidence of wear due to contact of the push rod with guide support assembly, P/N 5708625-3.

(2) Push rods showing evidence of wear shall, prior to further flight:

(i) be replaced either with an undamaged part; or

(ii) be reworked in accordance with the rework procedures outlined in Figure (1) of Step (7) of Douglas DC-8 Service Bulletin No. 27-51 Reissue No. 1 dated September 25, 1962, or an FAA approved equivalent. Push rods showing evidence of wear which require removal of material in excess of 0.025 inch in depth and one inch in length by 0.375 inch in width on one side of the push tube, or which have dents or sharp gouges, or are found worn or cracked in more than one area may not be reworked and must be replaced. When push rod assemblies are reworked, they must be reinspected using dye penetrant method or equivalent, to insure that no cracks exist after the rework is accomplished.

(3) Following reinstallation of push rod assemblies, and before further flight, conduct an initial check for clearance per Figure (1), Step (1); and , as necessary, accomplish the adjustment and rework outlined in Figure (1), Steps (2) through (6), of Douglas DC-8 Service Bulletin NO. 27-51, Reissue No. 1, dated September 25, 1962, or FAA approved equivalent.

(b) At intervals of not less than 400 nor more than 600 hours' time in service following the initial clearance check prescribed by (a)(3), unless other inspection intervals have been approved for an operator by the Chief, Engineering & Manufacturing Branch, FAA Western Region, remove and again inspect rods replaced or reworked per (a)(2) for any evidence of wear or contact with the guide support assembly. Any rods showing evidence of wear must be reworked or replaced per (a)(2), and the reinstallation clearance check and such adjustment and rework provisions of (a)(3), as found necessary, shall be accomplished.

(c) If, subsequent to compliance with (a), an airplane is altered by changing an elevator, elevator control tab, elevator control tab push rod assembly, or any combinations of these, the following new procedure is required:

(1) Prior to further flight conduct an initial check for clearance and any necessary adjustment and rework as described in (a)(3).

(2) At intervals of not less than 400 nor more than 600 hours' time in service following the initial clearance check required by (c)(1), unless other inspection intervals have been approved for an operator by the Chief, Engineering & Manufacturing Branch, FAA Western Region, the elevator control tab push rod assembly associated with this change shall be removed and inspected for any evidence of wear or contact with the guide support assembly as described in (a)(1). Any rods showing evidence of wear must be reworked or replaced as indicated in (a)(2) and the reinstallation clearance check and adjustment and rework provisions of (a)(3), as found necessary, shall be accomplished.

(d) The periodic reinspection prescribed by (b) and (c)(2) may be discontinued when:

(1) It is determined that no wear or contact with the guide support assembly has developed during the preceding reinspection interval, or

(2) The elevator control tab push-rod assembly Douglas P/N 3703218 is replaced with Douglas P/N 3703218-501, in accordance with the procedure outlined in DC-8 Service Bulletin No. 27-150 dated November 5, 1963, or by an FAA approved equivalent part and procedure.

NOTE: The P/N 3703218-501 steel push rods presently being installed during production have a smaller diameter than the original P/N 3703218 (no dash number) aluminum push rods.

(e) Upon request of the operator an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operation period of the operator if the request contains substantiating data to justify the increase or decrease for such operator.

(Douglas DC-8 Service Bulletins No. 27-51, Reissue No. 1, dated September 25, 1962, and No. 27-150, dated November 5, 1963, cover this same subject.)

This directive effective April 18, 1963.

Revised November 9, 1963.

Revised April 15, 1964.

Revised September 16, 1968.


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