| AD Number | 76-18-07 | Status | Active |
| Effective Date | September 10, 1976 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-2714 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Learjet Inc. |
| Model(s) | 24 25 35 36 |
76-18-07 GATES LEARJET: Amendment 39-2714. Applies to Models 24 (Serial Numbers 24-230 thru 24-331 and 24-333); 25 (Serial Numbers 25-061 and 25-067 thru 25-207); 35 (Serial Numbers 35-001 thru 35-079); and 36 (Serial Numbers 36-001 thru 36-020) airplanes.
Compliance: Required as indicated, unless already accomplished.
To determine that each inverter is connected to the correct power bus, within the next 25 hours' time in service after the effective date of this AD, accomplish the following in accordance with Gates Learjet Service Bulletins SB 24/25-273, dated August 9, 1976, or SB 35/36-24-3, dated August 9, 1976, or later approved revisions, as applicable:
A) Perform inverter operational check as outlined in the aforementioned Service Bulletins.
B) If the electrical system does not operate as indicated re the operational checks required by Paragraph A, rewire the inverter input power wiring per the applicable manufacturer's Service Manual Wiring Diagram and repeat the operational check required by Paragraph A to verify proper operation of the electrical system.
C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.
This amendment becomes effective September 10, 1976.