Airworthiness Directive · Amendment 39-15842 · Airbus Model A310 Series Airplanes and Model A300-600 Series Airplanes
Airbus Model A310 Series Airplanes and Model A300-600 Series Airplanes
Superseded. A later AD replaced this one: AD 2015-02-16. Comply with the one in force.
This AD applies to all Airbus Model A310 series airplanes; and Model A300-600 series airplanes; certificated in any category.
Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (q) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane.
This airworthiness directive (AD) supersedes two existing ADs. One AD applies to certain Airbus Model A310-200 and -300 series airplanes. That AD currently requires repetitive inspections for cracking of the flap transmission shafts, and replacement of the transmission shafts if necessary. That AD also provides an optional terminating action for the repetitive inspections. The other existing AD applies to all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model C4-605R Variant F airplanes (collectively called A300-600 series airplanes); and Model A310-200 and -300 series airplanes. That AD currently requires a one-time inspection of the trimmable horizontal stabilizer actuator (THSA), corrective actions if necessary, and follow-on repetitive tasks. This new AD also requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations and maintenance tasks for aging systems maintenance. This AD results from the manufacturer's determination that life limitations and maintenance tasks are necessary to ensure continued operational safety of the affected airplanes. We are issuing this AD to prevent reduced structural integrity of these airplanes due to the failure of system components.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
For Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, except for airplanes on which Airbus Modification 12247 has been embodied in production: At the earlier of the compliance times specified in paragraph (f)(1) or (f)(2) of this AD, perform a detailed inspection for stress corrosion cracking of the flight transmission shafts located between the power control unit (PCU) and the torque limiters in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005. Thereafter, repeat the inspections as required by paragraph (g) of this AD. Before further flight, replace any cracked transmission shaft discovered during any inspection required by this AD with a new or reconditioned shaft, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-27-2095, dated March 29, 2000. Doing an inspection in accordance with paragraph (n) or (o) of this AD terminates the requirements of this paragraph.
(1) Within 2,000 flight hours after the last flap asymmetry protection test performed in accordance with Airbus A310 Maintenance Planning Document (MPD) Task 275600-01-1.
(2) Within 8,000 flight cycles after the last flap asymmetry protection test performed in accordance with Airbus A310 MPD Task 275600-02-1 or 800 flight cycles after June 20, 2006 (the effective date of AD 2006-10-11), whichever comes later.
Note 2: Airbus Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005, refers to Lucas Liebherr Service Bulletin 551A-27-624, Revision 1, dated August 18, 2000, as a source of service information for accomplishing the inspections.
Note 3: Airbus Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005, refers to Airbus Service Bulletin A310-27-2095, dated March 29, 2000, as a source of information for replacing the flap transmission shafts.
Note 4: Airbus Service Bulletin A310-27-2095, dated March 29, 2000, refers to Lucas Liebherr Service Bulletin 551A-27-M551-05, dated January 12, 2000, as an additional source of information for replacing the flap transmission shafts.
Repeat the inspection required by paragraph (f) of this AD at the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. Doing an inspection in accordance with paragraph (n) or (o) of this AD terminates the requirements of this paragraph.
(1) Before further flight after any occurrence of jamming of the flap transmission system.
(2) At intervals not to exceed 2,000 flight hours after each flap asymmetry protection test performed in accordance with Airbus A310 MPD Task 275600-01-1.
(3) At intervals not to exceed 8,000 flight cycles after each flap asymmetry protection test performed in accordance with Airbus A310 MPD Task 275600-02-1.
Replacing any flap transmission shaft with a new or reconditioned transmission shaft in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-27-2095, dated March 29, 2000, ends the inspections required by paragraphs (f) and (g) of this AD for that transmission shaft only.
(i) Actions performed in accordance with Airbus Service Bulletin A310-27-2092, dated April 9, 1999; or Revision 01, dated December 11, 2001; are considered acceptable for compliance with the corresponding requirements of paragraphs (f) and (g) of this AD.
Although Airbus Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
At the applicable time specified in paragraph (k)(1) or (k)(2) of this AD, do a detailed inspection of specified components of the trimmable horizontal stabilizer actuator (THSA) in accordance with paragraph 1.E.(2)(a) and the Accomplishment Instructions of the applicable service bulletin as identified in Table 1 of this AD. Repair any discrepancy before further flight in accordance with TRW Aeronautical Systems Horizontal Stabilizer Actuator 47142 Series Component Maintenance Manual with Illustrated Parts List 27-44-13, Revision 6, dated September 14, 2001; or a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the European Aviation Safety Agency (EASA) (or its delegated agent). Doing an inspection in accordance with paragraph (n) or (o) of this AD terminates the requirements of this paragraph.
(1) If the flight hours accumulated on the THSA can be positively determined: Inspect at the earlier of:
(i) Before the accumulation of 47,000 total flight hours on the THSA, or within 600 flight hours after August 29, 2006 (the effective date of AD 2006-15-10), whichever occurs later.
(ii) Within 25 years since the THSA was new or within 600 flight hours after August 29, 2006, whichever occurs later.
(2) If the flight hours accumulated on the THSA cannot be positively determined: Inspect before the accumulation of 47,000 total flight hours on the airplane, or within 600 flight hours after August 29, 2006, whichever occurs later.
| Required Airbus Service Bulletin | Approved Airbus Service Bulletin version for actions done before the effective date of this AD | Airbus airplane model |
|---|---|---|
| Airbus Service Bulletin A300-27-6044, Revision 04, dated September 10, 2001; or Airbus Mandatory Service Bulletin A300-27-6044, Revision 05, dated August 29, 2006 | A300-27-6044, Revision 02, dated August 26, 2000; or Revision 03, dated June 28, 2001 | A300 B4-601, B4-603, B4-620, and B4-622. A300 B4-605R and B4-622R. A300 B4-605R and B4-622R. A300 C4-605R Variant F. |
| Airbus Service Bulletin A310-27-2089, Revision 02, dated June 28, 2001; or Airbus Mandatory Service Bulletin A310-27-2089, Revision 03, dated August 29, 2006 | A310-203, -204, -221, and -222. A310-304, -322, -324, and -325. |
Note 5: The service bulletins specified in Table 1 of this AD refer to Goodrich Actuation Systems Service Bulletin 47142-27-11, Revision 3, dated April 25, 2005, as an additional source of service information for the required actions.
Note 6: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
After the inspection required by paragraph (k) of this AD: Do the repetitive tasks in accordance with the Accomplishment Instructions and at the times specified in paragraph 1.E.(2)(b) of the applicable service bulletin identified in Table 2 of this AD, except as provided by paragraph (m) of this AD. The repetitive tasks are valid only until the THSA operational life exceeds 65,000 flight hours, 40,000 flight cycles, or 25 years, whichever occurs first. Before the THSA is operated beyond these extended life goals, it must be replaced with a new or serviceable THSA, except as required by paragraph (m) of this AD. Doing an inspection in accordance with paragraph (n) or (o) of this AD terminates the requirements of this paragraph.
| Required Airbus Service Bulletin | Approved Airbus Service Bulletin version for actions done before the effective date of this AD | Airbus airplane model |
|---|---|---|
| Airbus Service Bulletin A300-27-6044, Revision 04, dated September 10, 2001; or Airbus Mandatory Service Bulletin A300-27-6044, Revision 05, dated August 29, 2006 | A300-27-6044, Revision 02, dated August 26, 2000; or Revision 03, dated June 28, 2001 | A300 B4-601, B4-603, B4-620, and B4-622. A300 B4-605R and B4-622R. A300 B4-605R and B4-622R. A300 C4-605R Variant F. |
| Airbus Service Bulletin A310-27-2089, Revision 02, dated June 28, 2001; or Airbus Mandatory Service Bulletin A310-27-2089, Revision 03, dated August 29, 2006 | A310-27-2089, Revision 01, dated August 25, 2000 | A310-203, -204, -221, and -222. A310-304, -322, -324, and -325. |
Note 7: For additional information on the THSA life limits, refer to Airbus Operators Information Telex (OIT) SE 999.0074/05/BB, dated August 3, 2005.
For any THSA, whether discrepant or not, that is replaced with a new or serviceable THSA: Within 47,000 flight hours or 25 years, whichever occurs first, after the THSA is replaced, do the applicable tasks specified in paragraph 1.E.(2)(a) and the Accomplishment Instructions of the applicable service bulletin identified in Table 3. Thereafter repeat the tasks within the repetitive intervals specified in paragraph 1.E.(2)(b) of the applicable service bulletin. Doing the corresponding tasks in accordance with paragraph (n) or (o) of this AD terminates the requirements of this paragraph.
| Required Airbus Service Bulletin | Approved Airbus Service Bulletin version for actions done before the effective date of this AD | Airbus airplane model |
|---|---|---|
| Airbus Service Bulletin A300-27-6044, Revision 04, dated September 10, 2001; or Airbus Mandatory Service Bulletin A300-27-6044, Revision 05, dated August 29, 2006 | A300-27-6044, Revision 02, dated August 26, 2000; or Revision 03, dated June 28, 2001 | A300 B4-601, B4-603, B4-620, and B4-622. A300 B4-605R and B4-622R. A300 F4-605R and F4-622R. A300 C4-605R Variant F. |
| Airbus Service Bulletin A310-27-2089, Revision 02, dated June 28, 2001; or Airbus Mandatory Service Bulletin A310-27-2089, Revision 03, dated August 29, 2006 | A310-27-2089, Revision 01, dated August 25, 2000 | A310-203, -204, -221, and -222. A310-304, -322, -324, and -325. |
Within 3 months after the effective date of this AD, revise the ALS of the Instructions for Continued Airworthiness (ICA) to incorporate Airbus A310 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006 (for Model A310 series airplanes); or Airbus A300-600 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006 (for Model A300-600 series airplanes). For all tasks identified in Airbus A310 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; and Airbus A300-600 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; do the tasks at the later of the times specified in paragraphs (n)(1) and (n)(2) of this AD, as applicable, except as provided by paragraph (o) of this AD. The repetitive inspections must be accomplished thereafter at the interval specified in Airbus A310 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; or Airbus A300-600 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; as applicable. Doing an inspection required by this paragraph terminates the corresponding inspection required by paragraph (f), (g), (k), (l), or (m) of this AD.
(1) At the initial compliance times (thresholds) specified in Airbus A310 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; or Airbus A300-600 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; as applicable; with the compliance times starting from the later of the times specified in paragraphs (n)(1)(i) and (n)(1)(ii) of this AD.
(i) Since first flight of the airplane.
(ii) Since the applicable part was new or refurbished if the part's life (in flight hours, flight cycles, landings, or calendar time, as applicable) can be conclusively determined.
(2) Within 3 months after doing the revision of the ALS of the ICA required by paragraph (o) of this AD.
Note 8: For additional information on the THSA life limits, refer to Airbus OIT SE 999.0074/05/BB, dated August 3, 2005.
Note 9: For additional information on the THSA life limits and calculation method for unknown history of parts, refer to Airbus OIT SE 999.0008/07/LB, dated January 16, 2007; and Airbus Service Information Letter 05-008, Revision 01, dated February 21, 2007.
(o) For airplanes on which any life limitation/maintenance task has been complied with in accordance with the requirements of paragraph (f), (g), (k), (l), or (m) of this AD (e.g., AD 2006-10-11 or AD 2006-15-10), the last accomplishment of each limitation/task must be retained as a starting point for the accomplishment of each corresponding limitation/task interval now introduced in Airbus A310 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; and Airbus A300-600 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; as applicable. Doing an inspection required by this paragraph terminates the corresponding inspection required by paragraph (f), (g), (k), (l), or (m) of this AD.
(p) Except as provided by paragraph (q) of this AD: After accomplishing the actions specified in paragraphs (n) and (o) of this AD, no alternative inspection, inspection intervals, or limitations may be used.
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.
