| AD Number | 74-04-01 | Status | Active |
| Effective Date | February 12, 1974 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-1783 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Cessna Aircraft Company |
| Model(s) | 172 172A 172B 172C 172D 172E 172F (USAF T-41A) 172G 172H (USAF T-41A) 172I 172K 172L 172M 172N 172P 172Q 172R 172RG 172S |
74-04-01 CESSNA: Amdt. 39-1783. Applies to Model 172 (Serial Numbers 17260759 through 17261495, F17200905 through F-17201034 and FR17200351 through FR17200440) series airplanes.
Compliance: Required as indicated, unless already accomplished.
To detect cracks in the aft fuselage bulkhead assembly and provide means for repair of cracked assemblies, accomplish the following:
A) Within the next 100 hours' time in service after the effective date of this AD, visually inspect the aft fuselage bulkhead assembly (P/N 0512157-7) for cracks in accordance with Cessna Service Letter SE73-37 dated November 16, 1973, or later FAA-approved revisions.
B) If as a result of any inspection required herein, cracks are found, prior to further flight, repair the bulkhead assembly in accordance with Cessna Service Kit SK 172-44.
C) Any alternate methods of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.
Thisamendment becomes effective February 12, 1974.