AD 92-22-10

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AD Number:
92-22-10
Document Type:
AD Final Rules
Docket Number:
91-NM-222-AD
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-10 and KC-10A (Military) Series Airplanes
Subject:
Horizontal Stabilizer Cap & Panel
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/03/1992
Make:
The Boeing Company
Model:
DC-10-10 | DC-10-10F | DC-10-15 | DC-10-30 | DC-10-30F (KC-10A, KDC-10) | DC-10-40 | DC-10-40F
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Superseded AD: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Superseded By: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: 92-22-10
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   91-NM-222-AD

AMENDMENT:   39-8396

AD NUMBER:   92-22-10

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-10 and KC-10A (Military) Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 3, 1992.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   92-22-10 MCDONNELL DOUGLAS: Amendment 39-8396. Docket No. 91-NM-222-AD. Supersedes AD 87-06-53 R2, Amendment 39-6149.

Applicability: Model DC-10 and KC-10A (military) series airplanes, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent failure of the horizontal stabilizer rear upper spar cap and/or upper rear skin panel due to fatigue cracking, accomplish the following:

(a) Prior to the accumulation of 30,000 flight hours or 7,500 landings, whichever occurs earlier, or within 15 days after August 14, 1987 (the effective date of AD 87-06-53 R1, Amendment 39-5694), whichever occurs later, unless already accomplished within the last 120 days since August 14, 1987, conduct a dye penetrant or eddy current inspection of the horizontal stabilizer upper outer section rear spar cap and a visual inspection of the horizontal stabilizer upper outer rear skin panel, in accordance with the "Accomplishment Instructions" of McDonnell Douglas Alert Service Bulletin A55-18, dated March 23, 1987; or Revision 1, dated May 21, 1987; or Revision 2, dated February 8, 1988; or Revision 3, dated August 17, 1990; or Revision 4, dated September 10, 1991.

(b) Prior to the accumulation of 2,000 landings after accomplishing the inspections required by paragraph (a) of this AD, or within 100 landings after March 27, 1989 (the effective date of AD 87-06-53 R2, Amendment 39-6149), whichever occurs later, and thereafter at intervals not to exceed 2,000 landings, except as provided below, repeat the dye penetrant or eddy current inspection required by paragraph (a) of this AD.

(c) If the spar cap has been repaired by removing/blending out a crack in accordance with the method described in McDonnell Douglas Service Bulletin A55-18, Revision 2, dated February 8, 1988; or Revision 3, dated August 17, 1990; or Revision 4, dated September 10, 1991; repeat the dye penetrant or eddy current inspection of the spar required by paragraph (a) of this AD prior to the accumulation of 500 landings after the effective date of this amendment, or within 2,000 landings after the last inspection, whichever occurs first. Thereafter, repeat the dye penetrant or eddy current inspection at intervals not to exceed 500 landings.

(d) If the skin panel has been repaired by stop drilling a crack in accordance with the method described in McDonnell Douglas Service Bulletin A55-18, Revision 2, dated February 8, 1988; or Revision 3, dated August 17, 1990; or Revision 4, dated September 10, 1991; repeat the visual inspection of the skin panel required by paragraph (a) of this AD prior to the accumulation of 80 flight hours after the effective date of this AD, and thereafter at intervals not to exceed 80 flight hours.

(e) Conduct an eddy current inspection of the inboard-most end of the horizontal stabilizer rear spar cap upper vertical tang at station XRS-63.810, in accordance with either paragraph (e)(1) or (e)(2) of this AD.

(1) Within 90 days after the effective date of this AD: Conduct an eddy current inspection utilizing the "surface probe" method as described in McDonnell Douglas Service Bulletin A55-18, Revision 4, dated September 10, 1991, (hereafter referred to as the "Service Bulletin"). If no cracks are found, prior to the accumulation of 2,000 landings after the inspection, inspect the vertical tang in accordance with the "bolt hole" method described in the Service Bulletin. If no cracks are found as a result of the "bolt hole" method, prior to further flight, stress coin the attachment holes and install oversize attachments, in accordance with the Service Bulletin. Thereafter, at intervals not to exceed 3,500 landings, conduct an eddy current inspection utilizing the "surface probe" method, in accordance with the Service Bulletin.

(2) Prior to the accumulation of 1,000 landings after the effective date of this AD: Conduct an eddy current inspection in accordance with the "bolt hole" method as described in the Service Bulletin. If no cracks are found, prior to further flight, stress coin the attachment holes and install oversize attachments, in accordance with the Service Bulletin. Thereafter, at intervals not to exceed 3,500 landings, conduct an eddy current inspection utilizing the "surface probe" method, in accordance with the Service Bulletin.

(f) If any crack is found as a result of the inspections required by this AD, that is within the limits specified in the Service Bulletin, accomplish the procedures specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD, as applicable:

(1) For cracks in the spar cap that are within the limits specified in Table I of the Service Bulletin: Repair prior to further flight, in accordance with paragraph 4.(b) of the Service Bulletin.

(2) For cracks in the skin panel that are within the limits specified in Table II of the Service Bulletin: Repair prior to further flight, in accordance with paragraph 4.(c) of the Service Bulletin.

(3) For cracks in the vertical tang that are within the limits specified in paragraphs 4.3(a)(1), 4.3(a)(2) and 4.3(b) of the Service Bulletin: Repair prior to further flight, in accordance with 4.3(b) of the Service Bulletin.

(g) If any crack is found as a result of the inspections required by this AD that exceeds the limits specified in the Service Bulletin, prior to further flight, repair in a manner approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.

(h) 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, Los Angeles ACO, FAA, Transport 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, Los Angeles ACO.

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

(i) 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.

(j) The inspections and repairs shall be done in accordance with McDonnell Douglas Alert Service Bulletin A55-18, dated March 23, 1987; or McDonnell Douglas Alert Service Bulletin A55-18, Revision 1, dated May 21, 1987; or McDonnell Douglas Alert Service Bulletin A55-18, Revision 2, dated February 8, 1988; or McDonnell Douglas Alert Service Bulletin A55-18, Revision 3, dated August 17, 1990; or McDonnell Douglas Alert Service Bulletin A55-18, Revision 4, dated September 10, 1991; as applicable. 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 McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications - Technical Administrative Support, C1-L5B. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office (ACO), 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

This amendment 39-8396, AD 92-22-10, supersedes AD 87-06-53 R2, amendment 39-6149, which amended AD 87-06-53 R1, amendment 39-5694.

(k) This amendment becomes effective on December 3, 1992.

FOOTER: