What it approves
Modification to include provisions only for carriage and launch of Pegasus SIV satellite insertion vehicle (SIV).
What the certificate says
From the PDF’s text layer, without the form’s printed wording. Layout and order may differ; the PDF is the record.
FAA Form 8110-2 (3/21) SUPERSEDES PREVIOUS EDITION Number SA8011NM
This Certificate issued to Orbital Sciences LLC 17143 Flight Systems Drive Mojave, California 93501 Part 25* of the Federal Aviation Regulations.
Original Product - Type Certificate Number : A23WE Make :
Lockheed L-1011-385-1-15 Description of Type Design Change: Modification to include both provisions only, or for carriage and launch of the Pegasus Satellite Insertion Vehicle(s) (SIV) in accordance with FAA approved Orbital Sciences LLC Document Number L70001, revision C, dated September 30, 1998 or later FAA approved revision. See Continuation Sheets 3, 4, 5, 6, 7, and 8 for design configurations (Part 1, Part 2, Part 3, and Part 4) and applicable AFMS.
Limitations and Conditions: This installation defines both provisions only, or for carriage and launch of the Pegasus SIV and should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of the aircraft. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.
* Certification Basis Restricted Category for Configurations; Part 2, Part 3, and Part 4;
14 CFR part 21.25(a)(1), Special Purpose:
14 CFR part 21.25(b)(7), Space Vehicle Launch
- See Equivalent Safety Finding dated March 24, 1998 to 14 CFR § 25.1303(b)(l) and (c)(1) regarding the maximum airspeed pointer (VMO) and overspeed warning system.
Date of application : May 22, 1992
Date of issuance : August 17, 1994
Date reissued : June 22, 1995; September 29, 2000
Date amended : March 24, 1995; October 8, 1998;
September 29,2000; March 27, 2008; November 19, 2010 March 28, 2022
(Signature) Manager, Airframe Section Los Angeles ACO Branch
FAA Form 8110-2 (03/21) SUPERSEDES PREVIOUS EDITION Number SA8011NM
FAA Form 8110-2 (03/21) SUPERSEDES PREVIOUS EDITION Number SA8011NM
Date of Issuance: August 17, 1994 Date Amended: March 24, 1995, October 8, 1998, September 29, 2000, March 27, 2008 Date Reissued: June 22, 1995, September 29, 2000, November 19, 2010, March 28, 2022
Description of Type Design Change:: (continued)
Part 1 - Standard Category:
Provisions only for carriage and launch of Pegasus SIV: Notes 1, 2, 4, 6 and 7 apply for this configuration.
General
This airplane configuration is approved for transport category operations, provisions only, for carriage and launch of the Pegasus SIV when configured in accordance with FAA Approved "Item 1. Provisions Only" configuration, described in Orbital Sciences LLC Document Number L70001, Revision C dated September 30, 1998, or later FAA approved revision.
FAA Approved Flight Manual Supplement No. MA1 dated August 17, 1994, or later FAA Approved revisions, to basic Lockheed L-1011-385-1-15 LR25925 Flight Manual is required as a part of this approval for airplanes modified in accordance with FAA approved "Item I. Provisions Only" configuration, described in FAA approved Orbital Sciences LLC Document Number L70001, Revision C dated September 30, 1998, or later FAA approved revision.
Supplement No. MA1 contains Limitations, Procedures and Performance information required to operate the L-1011-385-1-15 with provisions only, that is when the Pegasus SIV is not attached and the aircraft is modified in accordance with FAA Approved "Item I. Provisions Only" configuration described in FAA approved Orbital Sciences LLC Document Number L70001, Revision C dated September 30, 1998, or later FAA approved revision.
OPERATING LIMITATIONS
Operating Limitations are unchanged from the basic LR25925 Flight Manual except as noted below.
MAXIMUM WEIGHTS Taxi 468,000 pounds Brake Release 466,000 pounds Landing 368,000 pounds MZFW 300,000 pounds
FAA Form 8110-2 (03/21) SUPERSEDES PREVIOUS EDITION
Date of Issuance: August 17, 1994 Date Amended: March 24, 1995, October 8, 1998, September 29, 2000, March 27, 2008 Date Reissued: June 22, 1995, September 29, 2000, November 19, 2010, March 28, 2022
Description of Type Design Change: (continued)
Part 2 - Restricted Category:
Carriage and Launch of Pegasus XL SIV: Notes 1, 3, 4, 6 and 7 apply for this configuration.
General
This airplane configuration is approved for restricted category operations, for carriage and launch of the Pegasus XL SIV when configured in accordance within FAA approved "Item 2. Carriage and Launch Pegasus XL rocket", described in FAA approved Orbital Sciences LLC Document Number L70001, Revision C dated September 30, 1998, or later FAA approved revision.
FAA Approved Flight Manual Supplement No. MA2 dated December 6, 1994, or later FAA Approved revision, to basic Lockheed L-1011-385-1-15 LR25925 Flight Manual is required as a part of this approval for airplanes configured in accordance with FAA approved "Item 2. Carriage and Launch of the Pegasus XL rocket", described in FAA approved Orbital Sciences LLC Document Number L70001, Revision C dated September 30, 1998, or later FAA approved revision.
Supplement No. MA2 contains Limitations, Procedures and Performance information required to operate the L-1011-385-1-15, for carriage and launch, that is when the Pegasus XL SIV is attached and the aircraft is configured in accordance with FAA approved "Item 2. Carriage and Launch Pegasus XL rocket", described in FAA approved Orbital Sciences LLC Document Number L70001, Revision C dated September 30, 1998, or later FAA approved revision.
OPERATING LIMITATIONS
Operating Limitations are unchanged from the basic LR25925 Flight Manual except as noted below.
MAXIMUM WEIGHTS Taxi 468,000 pounds Brake Release 466,000 pounds Landing 368,000 pounds MZFW 300,000 pounds (Note: When in launch or captive carry configuration the Maximum Zero Fuel Weight must be reduced by the weight of any fuel in tanks lA and 3A whenever tanks 1 and 3 are not full.)
Powerplant Limitations
Unchanged from basic Airplane Flight Manual
Operation of the APU is prohibited except when the airplane is stationary.
FAA Form 8110-2 (03/21) SUPERSEDES PREVIOUS EDITION
Date of Issuance: August 17, 1994 Date Amended: March 24, 1995, October 8, 1998, September 29, 2000, March 27, 2008 Date Reissued: June 22, 1995, September 29, 2000, November 19, 2010, March 28, 2022
Description of Type Design Change: (continued)
Performance Limitations
For all takeoff and landings:
Maximum permissible wind speed 30 knots Maximum crosswind component 20 knots Maximum tailwind component 10 knots
Autopilot/Flight Director
Airfield approach mode is limited to Category 1 coupled approach and the autopilot and autothrottle must be disengaged at 300 feet above airfield threshold altitude.
Part 3 - Restricted Category:
Carriage and Launch of Pegasus Hybrid: Notes 1, 3, 4, 6, and 7 apply for this configuration.
General
This airplane configuration is approved for restricted category operations, for carriage and launch of the Pegasus Hybrid SIV when configured in accordance within FAA approved "Item 3. Carriage and Launch of the Hybrid Pegasus rocket", described in Orbital Sciences LLC Document Number L70001, Revision C dated September 30, 1998, or later FAA approved revision.
FAA Approved Flight Manual Supplement No. MA2, Revision 3, dated August 8, 1998, or later FAA Approved revisions, to basic Lockheed L-1011-385-1-15 LR25925 Flight Manual is required as a part of this approval for airplanes configured in accordance with FAA approved "Item 3. Carriage and Launch of the Hybrid Pegasus rocket", described in FAA approved Orbital Sciences LLC Document Number L70001, Revision C dated September 30, 1998, or later FAA approved revision.
Supplement No. MA2, Revision 3, dated August 8, 1998, contains limitations, Procedures and Performance information required to operate the L-1011-385-1-15, for carriage and launch, that is when the Pegasus Hybrid SIV is attached and the aircraft is configured in accordance within FAA approved Item 3. Carriage and Launch of the Hybrid Pegasus rocket", described in FAA approved Orbital Sciences LLC Document Number L70001, Revision C dated September 30, 1998, or later FAA approved revision.
OPERATING LIMITATIONS
Operating Limitations are unchanged from the basic LR25925 Flight Manual except as noted below.
FAA Form 8110-2 (03/21) SUPERSEDES PREVIOUS EDITION
Date of Issuance: August 17, 1994 Date Amended: March 24, 1995, October 8, 1998, September 29, 2000, March 27, 2008 Date Reissued: June 22, 1995, September 29, 2000, November 19, 2010, March 28, 2022
Description of Type Design Change: (continued)
MAXIMUM WEIGHTS Taxi 468,000 pounds Brake Release 466,000 pounds Landing 368,000 pounds MZFW 300,000 pounds
Powerplant Limitations
Unchanged from basic Airplane Flight Manual
Operation of the APU is prohibited except when the airplane is stationary.
Performance Limitations
For all takeoff and landings:
Maximum permissible wind speed 30 knots Maximum crosswind component 20 knots Maximum tailwind component 10 knots
Autopilot/Flight Director
Airfield approach mode is limited to Category 1 coupled approach and the autopilot and autothrottle must be disengaged at 300 feet above airfield threshold altitude.
Part 4 - Restricted Category:
Carriage and Launch of Raytheon’s HAWC vehicle: Notes 1, 3, 4, 6 and 7 apply for this configuration.
General
This airplane configuration is approved for restricted category operations, for carriage and launch of the HAWC when configured in accordance within FAA approved "Item 4. Carriage and Launch of Raytheon’s HAWC vehicle", described in FAA approved Orbital Sciences LLC Document Number L70001, Revision R, dated December 15, 2021, or later FAA approved revision.
FAA Approved Flight Manual Supplement No. OS 56, dated March 24, 2022, or later FAA Approved revision, to basic Lockheed L-1011-385-1-15 LR25925 Flight Manual is required as a part of this approval for airplanes configured in accordance with FAA approved "Item 4. Carriage and Launch of Raytheon’s HAWC vehicle", described in FAA approved Orbital Sciences LLC Document Number L70001, Revision R, dated December 15, 2021, or later FAA approved revision.
FAA Form 8110-2 (03/21) SUPERSEDES PREVIOUS EDITION
Date of Issuance: August 17, 1994 Date Amended: March 24, 1995, October 8, 1998, September 29, 2000, March 27, 2008 Date Reissued: June 22, 1995, September 29, 2000, November 19, 2010, March 28, 2022
Description of Type Design Change: (continued)
Supplement No. OS 56 contains Limitations, Procedures and Performance information required to operate the L- 1011-385-1-15, for carriage and launch, that is when the HAWC is attached and the aircraft is configured in accordance with FAA approved "Item 4. Carriage and Launch of Raytheon’s HAWC vehicle", described in FAA approved Orbital Sciences LLC Document Number L70001, Revision R, dated December 15, 2021, or later FAA approved revision.
OPERATING LIMITATIONS
Operating Limitations are unchanged from the basic LR25925 Flight Manual except as noted below.
MAXIMUM WEIGHTS Taxi 468,000 pounds Brake Release 466,000 pounds Landing 368,000 pounds MZFW 300,000 pounds (Note: When in launch or captive carry configuration the Maximum Zero Fuel Weight must be reduced by the weight of any fuel in tanks 1A and 3A whenever tanks 1 and 3 are not full.)
Powerplant Limitations
Unchanged from basic Airplane Flight Manual
Operation of the APU is prohibited except when the airplane is stationary.
Performance Limitations
For all takeoff and landings:
Maximum permissible wind speed 30 knots Maximum crosswind component 20 knots Maximum tailwind component 10 knots
Autopilot/Flight Director
Airfield approach mode is limited to Category 1 coupled approach and the autopilot and autothrottle must be disengaged at 300 feet above airfield threshold altitude.
FAA Form 8110-2 (03/21) SUPERSEDES PREVIOUS EDITION
Date of Issuance: August 17, 1994 Date Amended: March 24, 1995, October 8, 1998, September 29, 2000, March 27, 2008 Date Reissued: June 22, 1995, September 29, 2000, November 19, 2010, March 28, 2022
Description of Type Design Change: (continued)
Other Operating Limitations:
Flight within 10NM of areas of thunderstorms activity or areas likely to result in sleet, hail, snow, or any form of electrical discharge is prohibited.
Flight into known areas of icing or severe turbulence is prohibited.
Notes: (applicable to Parts 1, 2, 3, and 4 as indicated above)
Notes
1) Carriage of personnel is restricted to a maximum of five persons in the cockpit, a maximum of two persons at the Launch Panel Operators (LPO) console and a maximum of twelve persons occupying the six double seats in the main cabin.
2) The nitrogen installation is limited to a maximum of 30 nitrogen cylinders. The maximum stored gas pressure must not exceed 1600 psi in any cylinder. Operation of the nitrogen system is prohibited.
3) Operation of the nitrogen installation is limited to a maximum of 30 nitrogen cylinders. The maximum stored gas pressure must not exceed 5000 psi in any cylinder.
4) This modification has been determined/demonstrated not to increase the noise level and is not considered an "acoustical change" as defined in Paragraph §2l.93(b), Amendment 21-75 of the Federal Aviation Regulations.
5) An amendment to the Lockheed L-1011 SID document LR92ER0060 must be FAA approved within 2000 operating hours, from the August 17, 1994 issue date of this STC, for continued operation of the L-1011-385-1-15.
6) Applicable Serial Number(s) of aircraft for Provisions Only, Pegasus XL, Pegasus Hybrid, and HAWC Modifications Include: 193E-1067
7) 14 CFR part 26 regulations:
Based on §§ 21.I 15 and 21.10 I and FAA Order 8I I 0.48, the certification basis for the L-1011-385-1-15 is as shown in TCDS A23WE for parts changed or affected by the change. Based on §21.10 I (g), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR pan 26 amendments, the holder of this STC must demonstrate compliance with the applicable sections. As of the issuance date of this STC, compliance has been found for the following regulations, § 26.11 (Arndt. 26-0).
Revised EWIS ICA has been approved by the Los Angeles Aircraft Certification Office. (Refer to § 26.11).
8) This aircraft must be operated with Rolls-Royce RB2 l l-524B4 engines installed with FAA approved Lockheed Martin Service Bulletin 093-71-050, Revision 2, dated March 26, 2008 or later FAA approved revision.
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ADs that name this STC · 0
An AD can apply because an STC is installed, or mention one in its text.
Approved models · 1
| Make | Model | Data sheet |
|---|---|---|
| Lockheed Aircraft Corporation | L-1011-385-1-15 | A23WE |
Every issue · 3
DRS keeps each issue of an STC as its own record, with its own certificate and attachments.
| Date | Status | Files |
|---|---|---|
| March 28, 2022 | Amended, current | Certificate |
| November 19, 2010 | Amended, earlier issue | Certificate |
| September 29, 2000 | Reissued, earlier issue | Certificate |