AD 92-16-19

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AD Number:
92-16-19
Document Type:
AD Final Rules
Docket Number:
92-NM-125-AD
Subject Heading:
Airworthiness Directives; Lockheed Aeronautical Systems Company Model L-1011-385 Series Airplanes
Subject:
Stabilizer Lower Actuator Pins
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/01/1992
Make:
Lockheed Martin Corporation
Model:
L-1011-385-1 | L-1011-385-1-14 | L-1011-385-1-15 | L-1011-385-3
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Superseded AD: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Superseded By: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: 92-16-19
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   92-NM-125-AD

AMENDMENT:   39-8329

AD NUMBER:   92-16-19

SUBJECT HEADING:   Airworthiness Directives; Lockheed Aeronautical Systems Company Model L-1011-385 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 1, 1992.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
92-16-19 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-8329. Docket No. 92-NM-125-AD. Supersedes AD 92-10-51, Amendment 39-8271.
Applicability: All Model L-1011-385 series airplanes, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent degradation of airplane pitch control, accomplish the following:

(a) Prior to the accumulation of 12,000 landings, or within 3 days after June 24, 1992 (the effective date of AD 92-10-51, Amendment 39-8271), whichever occurs later, accomplish the procedures specified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD:

(1) Gain access to the lower end of the stabilizer hydraulic actuators (four per airplane) where they attach to the front spar of the horizontal stabilizer center box structure at Fuselage Station FS 1875.

(2) Inspect for missing, sheared, or deformed stabilizer lower actuator attach pins, part number 1563117-101 (one per actuator).

(3) If any pin is missing, sheared, or deformed, replace the pin prior to further flight.

(b) At the applicable time specified in paragraph (b)(1), (b)(2), or (b)(3) of this AD, either perform a one-time magnetic particle inspection to detect cracks on each of the four lower horizontal stabilizer actuator pins (part number 1563117-101), or replace each of the four actuator pins (part number 1563117-101) with a new pin, in accordance with Lockheed Service Bulletin 093-27-304, Revision 1, dated May 28, 1992.

(1) For airplanes that have accumulated less than 12,000 landings as of the effective date of this AD: Prior to the accumulation of 12,000 landings, or within 60 days after the effective date of this AD, whichever occurs later.

(2) For airplanes that have accumulated at least 12,000 landings but not more than 20,000 landings as of the effective date of this AD: Within 45 days after the effective date of this AD.

(3) For airplanes that have accumulated more than 20,000 landings as of the effective date of this AD: Within 30 days after the effective date of this AD.

(c) If a magnetic particle inspection is performed in accordance with paragraph (b) of this AD, accomplish the procedures specified in paragraph (c)(1) or (c)(2), as applicable:

(1) If any actuator pin is found to be cracked: Prior to further flight, replace the cracked pin with a new pin, in accordance with Lockheed Service Bulletin 093-27-304, Revision 1, dated May 28, 1992. Thereafter, prior to the accumulation of 12,000 landings on each actuator pin, part number 1563117-101, it must be replaced with a new pin.

(2) If no actuator pins are found to be cracked: Prior to the accumulation of 1,000 landings after accomplishing the magnetic particle inspection, replace the pin with a new pin, in accordance with Lockheed Service Bulletin 093-27-304, Revision 1, dated May 28, 1992. Thereafter, prior to the accumulation of 12,000 landings on each actuator pin, part number 1563117-101, it must be replaced with a new pin.

(d) If each of the four actuator pins, part number 1563117-101, are replaced with a new pin in accordance with paragraph (b) of this AD: Thereafter, prior to the accumulation of 12,000 landings on each actuator pin, it must be replaced with a new pin.

(e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO.

NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO.

(f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(g) The inspection and replacement shall be done in accordance with Lockheed Service Bulletin 093-27-304, Revision 1, dated May 28, 1992, which contains the following list of effective pages:

Page Number
	
Revision Level
	
Date


1 - 8
	
1
	
May 28, 1992


9 - 11
	
Original
	
May 15, 1992

This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Lockheed Western Export Company (LWEC), Dept. 693, Zone 0755, 86 South Cobb Drive, Marietta, Georgia 30063. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the FAA, Atlanta Aircraft Certification Office, Suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street NW., 7th Floor, Suite 700, Washington, DC.

(h) This amendment becomes effective on September 1, 1992.

FOOTER: