Airworthiness Directive · Amendment 39-17944 · Periodic inspections
Airbus Airplanes
This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes, certificated in any category, all serial numbers.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by an analysis of the impacts of extended service goal activities on Airbus Model A300 series airplanes. This AD requires revising the maintenance or inspection program. We are issuing this AD to prevent failure of flight critical systems.
Within 90 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the information specified in Table 1 to paragraph (g) of this AD. The compliance time for doing the initial actions specified in Table 1 to paragraph (g) of this AD is before 60,000 total flight hours accumulated on the airplane, or within 90 days after the effective date of this AD, whichever occurs later.
| Maintenance planning document task No. | Task description | Interval (not to exceed) | Aircraft maintenance manual reference |
|---|---|---|---|
| 273311 0503 1 | ARTIFICIAL FEEL-ELEVATOR—Operational test of pitch artificial feel by comparing qualitatively operating loads in high-speed and low-speed configurations (with each individual hydraulic system) | 2,500 flight hours | 273300/501 |
| 273313 0503 1 | COMPUTER-ARTIFICIAL FEEL—Operational test of artificial feel “pitch feel” and “rudder travel” monitoring circuits (warning light test and indicating system test) | 3,500 flight hours | 272300/501 and 273300/501 |
| 222100 0503 1 | YAW DAMPER—Operational test to verify correct operation of mechanical control between yaw damper system 2 and the rudder | 80 flight hours | 222100/501 |
| 222600 0503 1 | YAW DAMPER—Operational test to verify correct operation of mechanical control between yaw damper system 2 and the rudder | 80 flight hours | 222600/501 |
| 272411 0503 1 | SERVO CONTROL-RUDDER—Operational test of rudder servo controls (with individual hydraulic system) by moving right-hand (RH) rudder pedal full forward and visually observe that rudder moves to the right. Check that rudder travel is confirmed on the flight control position indicator. Release RH pedal. Repeat above test by moving left-hand rudder pedal. | 250 flight hours | 271400/501 |
| 275400 0503 1 | FLAP ASYMMETRY—Operational test of flap asymmetry monitoring circuit (include solenoid operation) | 500 flight hours | 275400/501 |
| 275400 0503 2 | FLAP PRESSURE-OFF BRAKE—Operational test of pressure-off brake | 1,000 flight hours | 275400/501 |
| 278300 0503 1 | SLAT ASYMMETRY—Operational test of slat asymmetry monitoring circuit | 500 flight hours | 278300/501 |
| 278300 0503 2 | SLAT PRESSURE-OFF BRAKE—Operational test of pressure-off brake | 1,000 flight hours | 278300/501 |
As of the effective date of this AD, do not operate any airplane beyond 75,000 total flight hours or 48,000 total flight cycles, whichever occurs first.
After accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance in accordance with the procedures specified in paragraph (j)(1) 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.
