Airworthiness Directive · Amendment 39-14235 · Airbus Model A300 B2 and B4 Series Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310-200 and -300 Series Airplanes
Airbus Model A300 B2 and B4 Series Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310-200 and -300 Series Airplanes
Superseded. A later AD replaced this one: AD 2019-18-04. Comply with the one in force.
This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes; Model A300 B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-622R, C4-605R Variant F, F4-605R, and F4-622R airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes; certificated in any category.
The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B2 and B4 series airplanes; Model A300-600 series airplanes; and Model A310-200 and -300 series airplanes. That AD currently requires, among other actions, repetitive tests to detect desynchronization of the rudder servo actuators, and adjustment or replacement of the spring rods of the rudder servo actuators, if necessary. This new AD requires new repetitive tests/inspections/analyses of the rudder servo actuators, and related investigative/corrective actions if necessary. Accomplishment of the new actions ends the existing repetitive requirements. This AD is prompted by new reports of desynchronization of the rudder servo actuators. We are issuing this AD to prevent desynchronization of one of the three rudder servo actuators, which, if combined with an engine failure, could result in the loss of the related hydraulic system and could cause the loss of one of the two synchronized actuators. This condition could create additional fatigue loading and possible cracking on the attachment fittings and could result in the inability of the remaining synchronized actuator to maintain the commanded rudder deflection, which could result in reduced controllability of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Prior to accumulation of 1,300 total flight hours, or within 500 flight hours after July 30, 1998 (the effective date of AD 98-13-33), whichever occurs later, and thereafter at intervals not to exceed 1,300 flight hours: Perform a test to detect desynchronization of the rudder servo actuators in accordance with Airbus Service Bulletin A300-27-0188, Revision 2, dated October 1, 1997 (for Model A300 series airplanes); A300-27-6036, Revision 2, dated October 1, 1997 (for Model A300-600 series airplanes); or A310-27-2082, Revision 2, dated October 1, 1997 (for Model A310-200 and -300 series airplanes); as applicable. If any desynchronization (rudder movement) is detected, prior to further flight, either adjust or replace, as applicable, the spring rod of the affected rudder servo actuator in accordance with the applicable service bulletin.
Note 1: A test to detect desynchronization of the rudder servo actuators, if accomplished prior to the effective date of this AD in accordance with Airbus Service Bulletin A300-27-0188, dated October 24, 1996, or Revision 1, dated November 5, 1996 (for Model A300 series airplanes); A300-27-6036, dated October 24, 1996, or Revision 1, dated November 5, 1996 (for Model A300-600 series airplanes); or A310-27-2082, dated October 24, 1996, or Revision 1, dated November 5, 1996 (for Model A310-200 and -300 series airplanes); is considered acceptable for compliance with the initial test required by paragraph (f) of this AD.
(g) Except as provided by paragraph (h) of this AD, if any desynchronization (rudder movement) greater than the limit specified in Paragraph B of the Accomplishment Instructions of the applicable service bulletin is detected during any test required by paragraph (f) of this AD, prior to further flight, accomplish either paragraph (g)(1) or (g)(2) of this AD, in accordance with Airbus Service Bulletin A300-55-0044, dated October 22, 1996 (for Model A300 series airplanes); A300-55-6023, dated October 22, 1996 (for Model A300-600 series airplanes); or A310-55-2026, dated October 22, 1996 (for Model A310 series airplanes); as applicable.
(1) Conduct a visual inspection, high frequency eddy current inspection, or ultrasonic inspection, as applicable, to detect cracking of the rudder attachments; and repeat the inspection thereafter, as applicable, at the intervals specified in the applicable service bulletin. Or
(2) Modify the rudder attachments to cold expand the rivet holes.
(h) If any crack is found during any inspection or modification required by paragraph (g) of this AD, and the applicable service bulletin specifies to contact Airbus for an appropriate action: Prior to further flight, repair the affected structure in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or in accordance with a method approved by the Direction Générale de l'Aviation Civile (DGAC).
(i) The term “primary service bulletin,” as hereafter used in this AD, means the Accomplishment Instructions of the applicable primary service bulletin in Table 1 of this AD.
| Airbus service bulletin— | For— |
|---|---|
| (1) A300-27-0188, including Appendix 01 and Reporting Sheet, Revision 05, dated April 16, 2004 | Model A300 B2 and B4 series airplanes. |
| (2) A300-27-6036, including Appendix 01 and Reporting Sheet, Revision 08, dated April 16, 2004 | Model A300-600 series airplanes. |
| (3) A310-27-2082, including Appendix 01 and Reporting Sheet, Revision 05, dated April 16, 2004 | Model A310-200 and -300 series airplanes. |
(j) The primary service bulletin refers to the applicable secondary service bulletin in Table 2 of this AD as an additional source of service information for accomplishing the related investigative actions for certain conditions.
| Airbus service bulletin— | For— |
|---|---|
| (1) A300-55-0044, Revision 03, dated April 16, 2004 | Model A300 B2 and B4 series airplanes. |
| (2) A310-55-2026, Revision 02, dated April 16, 2004 | Model A310-200 and -300 series airplanes. |
| (3) A300-55-6023, Revision 05, dated April 16, 2004 | Model A300-600 series airplanes. |
Do the actions specified in paragraph (l) of this AD at the following times:
(1) Within 700 flight hours after the effective date of this AD or within 1,300 flight hours after the last inspection required by either paragraph (f) or (g) of this AD, whichever occurs first; and
(2) Thereafter at intervals not to exceed 1,300 flight hours.
Do the actions specified in paragraphs (l)(1) through (l)(4) of this AD and any applicable related investigative/corrective actions by doing all the actions in accordance with the primary service bulletin, except as required by paragraph (m) of this AD. Related investigative and corrective actions must be done before further flight. Accomplishing these actions ends the requirements of paragraphs (f) through (h) of this AD.
(1) Do an operational test of the rudder system with each hydraulic system pressurized in turn.
(2) Do a static inspection for correct synchronization of the rudder servo controls with each hydraulic system.
(3) Inspect to find dead travel of the input lever of the rudder servo control for each hydraulic system.
(4) Analyze the results of the static inspection required by paragraph (l)(2) of this AD and the inspection to find dead travel required by paragraph (l)(3) of this AD.
(m) If the primary/secondary service bulletin recommends contacting Airbus for appropriate action: Before further flight, repair any discrepancy in accordance with a method approved by either the Manager, International Branch, ANM-116; or the DGAC (or its delegated agent).
At the applicable time specified in paragraph (n)(1) or (n)(2) of this AD, submit a report only of positive findings in accordance with the primary service bulletin. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the action specified in the primary service bulletin was done after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the action specified in the primary service bulletin was accomplished before the effective date of this AD: Submit the report within 30 days after 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.
