What it approves
Installation of wing and tail engine pods.
What the certificate saysOCR
This is OCR from the scanned FAA certificate. OCR can misread letters and numbers.
United States of America S103 Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA3 139WE This certificate issued to: Rohr, Inc.
850 Lagoon Drive Chula Vista, California 91910-2098 part 25 of the Federa1 Aviation regulations * See page 4.
Original Product - Type Certificate Number: A22WE Make: McDonnell Douglas Model: DC-10-40 and -40F with FAA sealed Rohr drawing, Description of Type Design Change: Installation of wing and tail engine pods in accordance Revision "C" dated October 29, 1976, or later FAA approved revisions. DC-10-40 and -40F/JT9D-59A and -59B CNS, No. 196R0044, See Continuation Limitations and Conditions: (See continuation sheet page 3).
Date of Application: May 22, 1974 Date Reissued: December 20, 1976; July 21, 1992; February 28, 1995 Date of Issuance: March 24, 1916 Date Amended: November 5, 1976; May 18, 1978; March 15, 1979; August 26, 1980; May 14, 1986 FEDERAL AVIATION By Direction of the Administrator athu! tinne (Siggahre A → Kathy Skinner TOMINSTRATO Support Staff, ANM-1031 Acting Manager, Technical & Admin.
(Title)
FAA Form 8110-1(10-68) Page 1 of 4
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3139mE Date of Issuance: 3/24/76 Date Amended: 11/5/76; 5/18/78;
3/15/79; 8/26/80; 5/14/86 Date Reissued: 12/20/76; 7/21/92;
2/28/95 Limitations and Conditions: (Continued): This data sheet which is part of Supplemental Type Certificate product for which the Supplemental Type Certificate was issued meets the airworthiness of the Federal Aviation SA3139WE and applicable portions of Data Sheet A22WE, prescribes conditions and limitations under which the Regulations.
I - Model DC-10-40 (Transport Aircraft), Approved October 20, 1972 II - Model DC-10-40F (Transport Aircraft), Approved November 5, 1976 Engines 3 Pratt and Whitney Turbofan JT9D-59A or 598 Engines (See Serial Nos. Eligible) IT9D-59A IT9D-59B Static Thrust, Sea Level Engine Limits 51,720 Ibs. 53,230 Takeoff, Dry (5 min. flat to 84°F) Takeoff, Wet (2-1/2 min. wet flat to 86°F) Maximum Continuous 44,770 Ibs. 46,210 Maximum permissible engine rotor operating speeds 3780 грт N1 (Low compressor) 8011 pm N2 (High compressor) Maximum permissible engine temperature Turbine exhaust gas temperatures at turbine outlet T+7 Takeoff, Wet or Dry (5 min.) 1265°F(685°C) 1202°F(650°C) Maximum Acceleration (2 min.) Maximum Continuous Starting (Max. transient for 10 sec.) 1265°F(685°C) 941°F(505°C) Maximum permissible oil inlet temperature 248°F(120°) (Continuous Operation) (Transient Operation)* 320°F(160°C) *Transient operation above 248°F(120°C) is limited to 20 minutes.
Serial Numbers Eligible With JT9D-59A or -59B Engines 46974, 47822, 47823, 47824, 47825, 47826, 47852 46660-46662, 46913, 46920, 46923, 46966, 46967 47853, 47855, 47856, 47857, 48301 Note 1: The following oils are eligible for the JT9D-59A and -59B engines:
Oil specified in P & WA Spec. 521 (P & WA Service Bulletin 238)
FAA Form 8110-1(10-69) Page 3 of 4
United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3139WE Date of Issuance: 3/24/76 Date Amended: 11/5/76; 5/18/78;
3/15/79; 8/26/80; 5/14/86 Date Reissued: 12/20/76; 7/21/92;
2/28/95 Limitations and Conditions: The limitations and conditions of Type Certificate Data Sheet No. A22WE and FAA approved McDonnell Dougias Airplane Flight Manual No. MDC-J2140 (for the -59A engine) and Appendix XXI (for the -598 engine) apply. This approval is limited to installation in McDonnell Dougias DC-10-40 and -40F only.
This approval should not be extended to other specific airplanes of this model on which other previously approved modifications are incorporated, unless it is determined that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effects upon the airworthiness of that airplane.
*REGULATIONS:
FAR 25, February 1, 1965, Amendments 25-1 thru 25.22, 25.471 of 25-23. FAR 36, Special Conditions 25-18-WE-7 (January 7, 1970) & Amendment No. 1 July 9, 1971 & 25-46-WE-14 (October 16, 1972) SFAR 27 thru Amendment No. 2.
- End-
FAA Form 8110-1(10-69) Page 4 of 4
ADs that name this STC · 1
An AD can apply because an STC is installed, or mention one in its text.