Airworthiness Directive · Amendment 39-15156 · Airbus Model A300-600 Series Airplanes and Model A310 Series Airplanes
Airbus Model A300-600 Series Airplanes and Model A310 Series Airplanes
This AD applies to Airbus Model A300-600 series airplanes and Model A310 series airplanes, certificated in any category, equipped with carbon fiber reinforced plastic (CFRP) elevator skin panels, modified in accordance with Airbus Service Bulletin A310-55-2019 or A300-55-6016 (Airbus Modification 10861) with graphite fiber reinforced plastic (GFRP)/Tedlar film as external protection, with part numbers (P/Ns) and serial numbers (S/Ns) identified in Airbus Service Bulletin A300-55-6039 or A310-55-2040, both dated June 7, 2006.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300-600, A310-200, and A310-300 series airplanes. That AD currently requires inspecting for certain serial numbers on elevators, and doing a detailed inspection, visual inspection with a low-angle light, and tap-test inspection of the upper and lower surfaces of the external skins on certain identified elevators for any damage (i.e., debonding of the graphite fiber reinforced plastic/Tedlar film protection, bulges, debonding of the honeycomb core to the carbon fiber reinforced plastic, abnormal surface reflections, and torn-out plies), and doing corrective actions if necessary. This new AD also requires inspecting for damage of the identified elevators in accordance with a new repetitive inspection program, at new repetitive intervals; and would provide an optional terminating action for the repetitive inspections. This AD results from reports of damage caused by moisture/water inside the elevator. We are issuing this AD to detect and correct debonding of the skins on the elevators, which could cause reduced structural integrity of an elevator and 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.
Within 600 flight hours after February 3, 2006 (the effective date of AD 2005-26-17), inspect to determine if the S/N of the elevator is listed in Airbus All Operators Telex (AOT) A300-600-55A6032, dated June 23, 2004, or Airbus Service Bulletin A300-55-6039, dated June 7, 2006 (for Model A300-600 series airplanes); or in Airbus AOT A310-55A2033, dated June 23, 2004, or Airbus Service Bulletin A310-55-2040, dated June 7, 2006 (for Model A310 series airplanes).
(1) If the S/N does not match any S/N on either AOT or service bulletin S/N list, no further action is required by this paragraph.
(2) If the S/N matches a S/N listed in an AOT or service bulletin, before further flight, do the actions listed in Table 1 of this AD, and any corrective action as applicable, in accordance with Airbus AOT A300-600-55A6032, dated June 23, 2004; or Airbus AOT A310-55A2033, dated June 23, 2004; as applicable. Repeat the inspections thereafter at intervals not to exceed 600 flight hours until the inspection required by paragraph (j) of this AD is accomplished. Do applicable corrective actions before further flight.
| Do a— | Of the— | For any— |
|---|---|---|
| Detailed inspection | Elevator upper and lower external skin surfaces | Damage (i.e., breaks in the graphite fiber reinforced plastic (GFRP)/Tedlar film protection, debonded GFRP/Tedlar film protection, bulges, torn-out plies). |
| Visual inspection with a low-angle light | Elevator upper and lower external skin surfaces | Differences in the surface reflection. |
| Tap-test inspection | Upper and lower external skin surfaces of the honeycomb core panels in the elevator | Honeycomb core that has debonded from the carbon fiber reinforced plastic (CFRP). |
Note 1: 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 mirrors magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required.”
Where the AOTs specified in paragraph (f) of this AD say to contact the manufacturer for repair instructions, or an alternative inspection method: Before further flight, repair or do the alternative inspection method according to a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Gonorale de l'Aviation Civile (DGAC) (or its delegated agent), or the European Aviation Safety Agency (EASA) (or its delegated agent).
As of February 3, 2006, no carbon fiber elevator having part number (P/N) A55276055000 (left-hand side) or P/N A55276056000 (right-hand side) may be installed on any airplane unless it is inspected according to paragraph (f) of this AD; or according to paragraph (j) of this AD.
(i) Although the AOTs referenced in paragraph (f) of this AD specify to submit inspection reports to the manufacturer, this AD does not include that requirement.
For airplanes with affected serial numbers identified in paragraph (f) of this AD: Except as provided by paragraph (k) of this AD, within 2,000 flight cycles or 18 months after the effective date of this AD, whichever occurs earlier, do a detailed inspection of the external surfaces of the GFRP/Tedlar film protection on the upper and lower skin panels to detect damage of the film, and a thermographic inspection of the upper and lower skin panels to detect any potential water indication inside the panel's honeycomb core; do all applicable related investigative/corrective actions before further flight; and repair the external GFRP/Tedlar film with pore filler. Do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-55-6039 (for Model A300-600 series airplanes), or Airbus Service Bulletin A310-55-2040 (for Model A310 series airplanes); both including Appendix 01, both dated June 7, 2006. Repeat the inspections thereafter at intervals not to exceed 2,000 flight cycles or 18 months, whichever occurs earlier. Where the service bulletin says to contact the manufacturer for repair instructions: Before further flight, repair or do the alternative inspection method according to a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent). Doing the inspections in accordance with this paragraph terminates the repetitive inspection requirements of paragraph (f) of this AD.
(k) The maximum time between the inspection required by paragraph (f) of this AD and the first inspection done in accordance with paragraph (j) of this AD must be no greater than: For the thermographic inspection, 2,500 flight hours after the last thermographic inspection done in accordance with the applicable AOT specified in paragraph (f) of this AD; and for the tap test, 600 flight hours after the last tap test inspection done in accordance with the applicable AOT specified in paragraph (f) of this AD.
Submit a report of the findings (both positive and negative) of the inspections required by paragraph (j) of this AD to Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, at the applicable time specified in paragraph (l)(1) or (l)(2) of this AD. The report must include the information in Appendix 01 of Airbus Service Bulletin A300-55-6039 or Airbus Service Bulletin A310-55-2040, both dated June 7, 2006, as applicable. Under the provisions of the Paperwork Reduction Act (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 inspection was done after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
Replacing the external GFRP/Tedlar film with an application of pore filler on the whole elevator external surface in accordance with Airbus Service Bulletin A300-55-6040 (for Model A300-600 series airplanes), or Airbus Service Bulletin A310-55-2041 (for Model A310 series airplanes), both dated June 5, 2006, terminates the repetitive inspection requirements of paragraph (j) of this AD, provided the replacement is done before further flight after accomplishment of Airbus Service Bulletins A310-55-2040 and A300-55-6039, both dated June 7, 2006.
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.
