Airworthiness Directive · Amendment 39-14982 · Raytheon Aircraft Company Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) Airplanes
Raytheon Aircraft Company Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) Airplanes
Superseded. A later AD replaced this one: AD 2007-06-01 R1. Comply with the one in force.
This AD affects the following airplane models and serial numbers that are certificated in any category:
| Model | Serial numbers |
|---|---|
| Beech 45 (YT-34) | All |
| Beech A45 (T34A, B-45) | All |
| Beech D45 (T-34B) | All |
We are adopting a new airworthiness directive (AD) that supersedes AD 62-24-01, which applies to all Raytheon Aircraft Company (RAC) Beech Models 45 (YT-34), A45 (T-34A, B45), and D45 (T-34B) airplanes. AD 62-24-01 currently requires you to repetitively inspect, using the dye penetrant method, the front and rear horizontal stabilizer spars for cracks and replace any cracked stabilizer. Since we issued AD 62-24-01, we determined that using the dye penetrant inspection method may not detect cracks before the crack grows to a critical length and causes failure of the horizontal stabilizer spars. Therefore, we are requiring the surface eddy current inspection method to detect cracks in the horizontal stabilizer spars. Consequently, this AD retains the actions required in AD 62-24-01 and changes the required inspection method from dye penetrant to surface eddy current. We are issuing this AD to prevent failure of the front and/or rear horizontal stabilizer spars caused by fatigue cracks. This failure could result in stabilizer separation and loss of control of the airplane.
Using the surface eddy current inspection procedures outlined in the appendix of this AD, inspect the front and rear horizontal stabilizer spars between the butt rib and the inboard end for cracks, unless already done, as follows:
(1) If the last inspection of the front and rear horizontal stabilizer spars was done using the surface eddy current method (or FAA-approved equivalent method) to show compliance with AD 62-24-01 and/or to show compliance with the alternative method of compliance (AMOC) to AD 2004-25-51: Repetitively inspect thereafter at intervals not to exceed 500 hours time-in-service (TIS).
(2) If the last inspection of the front and rear horizontal stabilizer spars required by AD 62-24-01 was done using the dye penetrant method: Inspect initially as presented in the table below and repetitively thereafter at intervals not to exceed 500 hours TIS:
| If | Then |
|---|---|
| (i) Less than 200 hours TIS have passed since the last inspection required by AD 62-24-01: | Inspect at whichever of the following occurs later: |
| (A) Upon accumulating 200 hours TIS since the last inspection required by AD 62-24-01; or | |
| (B) Within the next 6 months after April 16, 2007. (the effective date of this AD). | |
| (ii) If 200 hours TIS or more have passed since the last inspection required by AD-24-01: | Inspect at whichever of the following occurs first, unless paragraph (e)(2)(iii) of this AD applies, as specified below: |
| (A) At the next repetitive inspection required by AD 62-24-01; or | |
| (B) Within the next 6 months after April 16, 2007 (the effective date of this AD). | |
| (iii) If paragraph (e)(2)(ii) results in the initial surface eddy current inspection becoming mandatory within 30 days after the effective date of this AD: | Inspect within the next 30 days after April 16, 2007. (the effective date of this AD). |
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
