# AD 68-19-02: Cracks in Lower Fuselage

- Type: Airworthiness directive
- Status: Current
- Products: Aermacchi S.205 - 22/R
- Effective: October 11, 1968
- Superseded by: Nothing supersedes this AD
- Product type: Aircraft, Small airplane
- Amendment: 39-654
- Registered aircraft: 22 may be affected, by airframe or engine model (OpenAirDocs)
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/90629AA362FB244486256A550066F2E2.0001
- DRS record last changed: May 30, 2024
- Page: https://openairdocs.org/ad/68-19-02

## The airworthiness directive

68-19-02 SIAI-MARCHETTI: Amendment 39-654. Applies to Model S.205/22R airplanes, Serial Nos. 213, 370, 371, 372, 373, 374, 378, 379, 380, 381, 382, 384, 385, 386, 387, 388, 389, 390, 392, 393, 394, 395, 396, 398, 4-124, 4-125, 4-132, 4-142, 4-143, 4-145, 4-146, 4- 147, 4-148.

Compliance required as indicated, unless already accomplished.

To detect cracks in the lower part of fuselage frame No. 2, at the rudder control bellcrank brackets, and to detect cracks and deformation in the stringers of the fuselage belly skin which are located at the outboard rudder pedal support tube brackets, accomplish the following:

  (a) Within the next 10 hours' time in service after the effective date of this AD, visually inspect, using a lamp and mirror, the lower portion of fuselage frame No. 2 for cracks and the lower fuselage stringers for cracks and deformation in accordance with Siai Service Bulletin No. 205B20, dated March 22, 1968, or later RAI-approved revision or an FAA-approved equivalent. If no cracks are found, comply with paragraph (d) within the next 100 hours' time in service after the effective date of this AD.

  (b) If cracks are found during the inspection required by paragraph (a) none of which exceed 3/16 inches in length, repeat that inspection at intervals not to exceed 20 hours' time in service from the last inspection and comply with paragraph (d) within the next 100 hours' time in service after the effective date of this AD. The repetitive inspection required in this paragraph may be discontinued upon compliance with paragraph (d).

  (c) If cracks are found during the inspection required by paragraph (a) which exceed 3/16 inches in length, comply with paragraph (d) before the next flight.

  (d) Modify fuselage frame No. 2 and stringers in accordance with Siai Service Bulletin No. 205B20, dated March 22, 1968, or later RAI-approved revision, or an FAA- approved equivalent.

This amendment becomes effective October 11, 1968.

## Affected data sheets (1) (OpenAirDocs)

The type certificate data sheets whose models the AD names.

- [TCDS A9EU](https://openairdocs.org/tcds/A9EU): Aermacchi S.p.A.; names 1 of 7 models: S.205 - 22/R

## Registered aircraft it may apply to (OpenAirDocs)

Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment.

- Aircraft: 22 (22 by airframe model, 0 by engine model)
- Makers: Siai-Marchetti 22

Models with the most aircraft:

- [Siai-Marchetti S.205/22R](https://openairdocs.org/model/siai-marchetti-s-205-22r): 22 aircraft (airframe model)

All 1 models: https://openairdocs.org/ad/68-19-02/models.md
Every aircraft: https://openairdocs.org/ad/68-19-02/aircraft.md

Its text cites no advisory circulars or STCs.

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.