| AD Number | 73-14-03 | Status | Active |
| Effective Date | July 06, 1973 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-1679 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Textron Aviation Inc. |
| Model(s) | 58 58A 95-B55 95-B55A A36 E55 E55A F33A F33C V35B |
73-14-03 BEECH: Amendment 39-1679. Applies to: 1) Paragraphs A and C of the AD are applicable to: Model F33A (Serial Numbers CE-400 through CE-414, CE-416 through CE- 426, CE-428 and CE-432); Model F33C (Serial Numbers CJ-31 (CD-1305) through CJ-39 (CD- 1313)); Model V35B (Serial Numbers D-9389 through D-9406, D-9408 through D-9454 and D- 9464); Model A36 (Serial Numbers E-362 through E-367, E-369 through E-389, E-392 through E-409, E-415, E-417 and E-418); Models 95-B55 and 95-B55A (Serial Numbers TC-1484, TC-1486 through TC-1533, TC-1538, TC-1542 and TC-1544); Models E55 and E55A (Serial Numbers TE-880, and TE-882 through TE-907); Models 58 and 58A (Serial Numbers TH-264, TH-266 through TH-310, TH-315 and TH-318).
Applies to: 2) Paragraphs A, B, and C of the AD are applicable to: Model F33A (Serial Numbers CE-427, CE-430 and CE-431); Model V35B (Serial Numbers D-9455 through D-9460 and D-9462); Model A36 (Serial Numbers E-410 through E-414 and E-416); Models 95-B55 and 95-B55A (Serial Numbers TC-1534 through TC-1537); Models E55 and E55A (Serial Numbers TE-908, TE-909 and TE-910); Models 58 and 58A (Serial Numbers TH-311 through TH-314 and TH-316).
Compliance: Required as indicated, unless already accomplished per Beechcraft Service Instructions 0579-200 or later FAA-approved revisions.
To check landing gear shock strut pistons for proper hardness, within the next 100 hours' time in service after the effective date of this AD, accomplish the following:
A) Using a portable hardness tester, measure the hardness of the nose gear shock strut piston in an area from 1 inch to 4 inches above the nose wheel fork. The allowable hardness range is from Rockwell Scale C38 to C46 1/2. If during the hardness measuring process a reading appears unreliable, make additional measurements at other spots but within the 1 inch to 4 inch area specified herein until an accurate measurement is obtained.
B) Using a portable hardness tester, measure the hardness of both main gear shock strut pistons in an area 1 inch to 4 inches above the axle socket. The allowable hardness range is from Rockwell Scale C43 1/2 to C50 1/2. If during the hardness measuring process a reading appears unreliable, make additional measurements at other spots but within the 1 inch to 4 inch area specified herein until an accurate measurement is obtained.
C) If a hardness measurement is outside of the hardness range specified in Paragraphs A and/or B of this AD, prior to further flight, replace any defective landing gear shock strut piston with an airworthy piston, except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement can be performed, provided the landing gear remains down and locked.
This amendment becomes effective July 6, 1973.