# STC SA5510NM - Type: Supplemental type certificate - Status: Current, Amended - Holder: Structural Integrity Engineering, United States - Description: Modification in accordance with FAA approved SIE Drawing List 9000 N/C,, dated August 7, 1991, or later FAA approved revisions, to permit an increased maximum zero fuel weight (MZFW), and maximum landing weight (MLW) of DC-8-61 airplanes. - Applied: January 22, 1990 - Status date: December 29, 2003 - Product: Aircraft, Large Multi-Engine - Certification basis: Part 21, Part 36 - Data sheets: [TCDS 4A25](https://openairdocs.org/tcds/4A25) - Certificate PDF: https://openairdocs.org/files/sha256/82/65/82654ff14becb61909c7c569ba8697d6a7621040ce14c86f985737c2f60adfc2 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/444DB44B2EEB3FD586256E6E006FFF3D.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SA5510NM ## ADs that name it (0) None. ## Approved models (1) - McDonnell Douglas Corporation DC-8-61 ([TCDS 4A25](https://openairdocs.org/tcds/4A25)) ## What the certificate says Read from the PDF's text layer, without the form's printed wording; the layout is lost and the order can differ. The PDF is the record. Number SA5510NM Structural Integrity Engineering 9525 Vassar Avenue Chatsworth, California 91311 This Certificate issued to Part 4b* of the Civil Air Regulations. *Certification basis is set forth in Type Certificate Data Sheet A3WE. 4A25 McDonnell Douglas DC-8-61 Original Product Type Certificate Number : Description of Type Design Change: Modification in accordance with FAA approved SIE Drawing List 9000 "N/C", dated August 7, 1991, or later FAA approved revisions, to permit an increased maximum zero fuel weight (MZFW), and maximum landing weight (MLW) of DC-8-61 airplanes. Limitations and Conditions: This approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of that aircraft. (See Continuation Sheets 3 , 4 and 5 for applicable serial numbers and revised zero fuel and maximum landing weights). Date of application : January 22, 1990 Date of issuance : January 8, 1992 Date reissued : December 29, 2003 Date amended : May 19, 1992; December 15, 1992; March 18, 1994; June 14, 1995; September 7, 2000 ( Signature) Manager, Technical & Administrative Support Staff, Los Angeles Aircraft Certification Office (Title) Number SA5510NM For aircraft with acoustically treated nacelles in accordance with STC's SA2411SO and SA5670NM jointly, the approval of this change in type design applies only to McDonnell Douglas DC-8-61 airplanes with the following Serial Numbers:45887, 45890, 45891, 45893, 45942, 45964. FAA approved SIE Airplane Flight Manual Supplement, Report No. SIE 11-602 Revision "A", dated May 13, 1992, or later FAA approved revisions, to the basic DC-8-61 Airplane Flight Manual, DAC-33161, is required as a part of this approval for these DC-8-61 model airplanes modified in accordance with FAA approved SIE Drawing List 90000, Rev. N/C, dated August 7, 1991. FAA approved SIE Airplane Flight Manual Supplement, Report No. SIE 11-603 Original Issue, dated December 15, 1992, or later FAA approved revisions, to the basic DC-8-61 Airplane Flight Manual, DAC- 33161, is required as a part of this approval for these DC-8-61 model airplanes modified in accordance with FAA Approved SIE Drawing List 90000, Rev. A, dated October 21, 1992, or later FAA approved revisions. The following data have superseded those in the Model DC-8-61 Type Data Sheet 4A25, Revision 31, Section XV. Maximum Zero Fuel Weight Limits: 234,000 lbs. Maximum Landing Weight Limits: 252,000 lbs. Noise: For compliance to 14CFR part 36, STC’s SA2411SO and SA5670NM must be installed prior to or concurrent with this modification. For aircraft equipped with acoustically treated nacelles, in accordance with STC SA2106SO, the approval of this change in type design applies only to McDonnell Douglas DC-8-61 airplanes with the following Serial Numbers: None at this time. FAA approved SIE Airplane Flight Manual Supplement, Report No. SIE-11-601 Original Issue, dated January 6, 1992, or later FAA approved revisions, to the basic DC-8-61 Airplane Flight Manual, DAC- 33161, is required as a part of this approval for these DC-8-61 model airplanes. The following data supersede those in the Model DC-8-61 Type Data Sheet 4A25 Revision 31, Section XV: Maximum Zero Fuel Weight Limits: 234,000 lbs Maximum Landing Weight Limits: 248,000 lbs Number SA5510NM Noise: For compliance to 14CFR part 36, STC SA2106SO must be installed prior to or concurrent with this modification. Weight and Balance Manual Supplements which limit the zero fuel weight center of gravity, the landing weight, the takeoff weight, and the zero fuel weight are required as per the appropriate Airplane Flight Manual Supplements referenced above. The inspection intervals of 3,600 hours called out in AD-80-22-01, Lower Inboard Aft Spar Cap and Skin, and in AD-84-13-02, Lower Wing Front Spar Cap, are to be reduced to 3,000 hours. For aircraft with acoustically treated nacelles in accordance with STC SA3915NM, the approval of this change in type design applies only to McDonnell Douglas DC-8-61 airplanes with the following Serial numbers: 45890, 45942. FAA approved SIE Airplane Manual Supplement, Report No. SIE 11-604, Revision NC dated June 21, 1993, or later FAA approved revisions, to the basic DC-8-61 Airplane Flight Manual, DAC-33161, is required as a part of his approval for these DC-8-61 model airplanes modified in accordance with FAA approved SIE Drawing List 90000, Revision B, dated June 9, 1993. The following data have superseded those in the Model DC-8-61 Type Data Sheet 4A25, Revision 31, Section XV. Maximum Zero Fuel Weight Limits: 234,000 lbs. Maximum landing Weight limits: 248,000 lbs. Noise: For compliance to 14CFR part 36, either STC SA3915NM alone or both STCs SA2411SO and STC SA5760NM must be installed prior to or concurrent with this modification. For aircraft equipped with acoustically treated nacelles, in accordance with STC SA01380AT, the approval of this change in type design applies only to McDonnell Douglas DC-8-61 airplanes with the following Serial Numbers: 45888, 46159. FAA approved SIE Airplane Flight Manual Supplement, Report No. SIE-11-605 Original Issue, dated September 7, 2000, or later FAA approved revisions, to the basic DC-8-61 Airplane Flight Manual, DAC- 33161, is required as a part of this approval for these DC-8-61 model airplanes. The following data supersede those in the Model DC-8-61 Type Data Sheet 4A25 Revision 31, Section XV: Maximum Zero Fuel Weight Limits: 234,000 lbs Maximum Landing Weight Limits: 252,000 lbs Noise: For compliance to 14CFR part 36, STC SA01380AT must be installed prior to or concurrent with this modification. Weight and Balance Manual Supplements which limit the zero fuel weight center of gravity, the landing weight, the takeoff weight, and the zero fuel weight are required as per the appropriate Airplane Flight Manual Supplements referenced above. - END - ## Every issue (1) - December 29, 2003: Amended, Current. [certificate](https://openairdocs.org/files/sha256/82/65/82654ff14becb61909c7c569ba8697d6a7621040ce14c86f985737c2f60adfc2) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.