Airbus has also issued Service Bulletin A300556040 (for Model A300600 series airplanes) and Service Bulletin A310552041 (for Model A310 series airplanes), both dated June 5, 2006. The service bulletins describe procedures for replacing the external GFRP/Tedlar film with an application of pore filler on the whole elevator external surface. Doing this replacement eliminates the need for the repetitive inspections.

Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The EASA mandated the service information and issued EASA airworthiness directive 2006 0289, dated November 2, 2006, to ensure the continued airworthiness of these airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

These airplane models are manufactured in France and type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. As described in FAA Order 8100.14A, ``Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,'' dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA's findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States.

This proposed AD would supersede AD 20052617 and would retain the requirements of the existing AD. This proposed AD would also require accomplishing the actions specified in the service information described previously, except as discussed under ``Difference between the Proposed AD and the EASA Airworthiness Directive.''
Difference Between the Proposed AD and the EASA Airworthiness Directive

The EASA airworthiness directive specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions using a method that we or the EASA (or its delegated agent) approve. In light of the type of repair that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, a repair we or the EASA approve would be acceptable for compliance with this proposed AD.

Changes to Existing AD

We have clarified the applicability of the existing AD to more closely match the language of the applicability of the EASA airworthiness directive.

Paragraph (g) of the existing AD specifies making repairs or doing alternative inspections using a method approved by either the FAA or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated agent). The EASA has assumed responsibility for the airplane models subject to this proposed AD. Therefore, we have revised paragraph (g) of this proposed AD to specify making repairs or doing alternative inspections using a method approved by the FAA, the DGAC (or its delegated agent), or the EASA (or its delegated agent). Clarification of Inspection Terminology

In this proposed AD, the ``detailed visual inspection'' specified in the Airbus service bulletin is referred to as a ``detailed inspection.'' We have included the definition for a detailed inspection in a note in the proposed AD.

Interim Action

We consider this proposed AD interim action. We are currently considering requiring the optional terminating action of replacing the external GFRP/Tedlar film with an application of pore filler on the whole elevator external surface, which would constitute terminating action for the repetitive inspections required by this AD action. Costs of Compliance

This proposed AD would affect about 142 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. The average labor rate is $80 per work hour.
Estimated Costs Action Work hours Parts Cost per airplane Fleet cost Inspection for serial number 1................. $0................ $80............... $11,360. (required by AD 20052617).
Repetitive inspections (required 3................. 0................. $240, per $34,080, per by AD 20052617). inspection cycle. inspection cycle. New repetitive inspection Between 8 and 12.. 0................. Between $640 and Between $90,880 program (new proposed action). $960, per and $136,320, per inspection cycle. inspection cycle. Replacement (optional 48................ 90................ $3,930............ $558,060. terminating/new proposed
action).

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We have determined that this proposed AD would not have federalism implications under Executive Order
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13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that the proposed regulation:

1. Is not a ``significant regulatory action'' under Executive Order 12866;

2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by removing amendment 3914438 (70 FR 77301, December 30, 2005) and adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA200728159; Directorate Identifier 2006NM 257AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by June 15, 2007.
Affected ADs
(b) This AD supersedes AD 20052617.
Applicability
(c) This AD applies to Airbus Model A300600 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 A31055 2019 or A300556016 (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 A300556039 or A310552040, both dated June 7, 2006.
Unsafe Condition
(d) 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.
Compliance
(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Restatement of the Requirements of AD 20052617
Inspection for Serial Number, Repetitive Inspections, and
Corrective Actions
(f) Within 600 flight hours after February 3, 2006 (the effective date of AD 20052617), inspect to determine if the S/N of the elevator is listed in Airbus All Operators Telex (AOT) A300600 55A6032, dated June 23, 2004, or Airbus Service Bulletin A30055 6039, dated June 7, 2006 (for Model A300600 series airplanes); or in Airbus AOT A31055A2033, dated June 23, 2004, or Airbus Service Bulletin A310552040, 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 A30060055A6032, dated June 23, 2004; or Airbus AOT A31055A2033, 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.
Table 1.Repetitive Inspections
Do a Of the For any Detailed inspection......... Elevator upper and Damage (i.e., breaks lower external skin in the graphite surfaces. fiber reinforced plastic (GFRP)/ Tedlar film protection, debonded GFRP/ Tedlar film protection, bulges, tornout plies). Visual inspection with a low Elevator upper and Differences in the angle light. lower external skin surface reflection. surfaces.
Taptest inspection......... Upper and lower Honeycomb core that external skin has debonded from surfaces of the the carbon fiber honeycomb core reinforced plastic panels in the (CFRP). elevator.

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.''
Repair Approval
(g) Where the AOT specified in paragraph (f) of this AD says 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, ANM116, FAA, Transport Airplane Directorate; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated agent), or the European Aviation Safety Agency (EASA) (or its delegated agent).
Parts Installation
(h) As of February 3, 2006, no carbon fiber elevator having part number (P/N) A55276055000 (lefthand side) or P/N A55276056000 (righthand 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.
No Reporting Required for AOT Inspections
(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.
New Requirements of This AD
Revised Inspection Program
(j) For airplanes with affected S/Ns 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 GRFP/Tedlar film protection on the upper and lower skin panels to detect damage of the film, and a
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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 Service Bulletin A300556039 (for Model A300600 series airplanes), or Service Bulletin A310552040 (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, ANM116, FAA, Transport Airplane Directorate; or the European Aviation Safety Agency (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 paragraph (f) of this AD.
Report
(l) 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 A300556039, or Service Bulletin A310552040, 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 21200056.
(1) If the inspection was done after the effective date of this

FOR FURTHER INFORMATION CONTACT Tom Stafford, Aerospace Engineer, International Branch, ANM116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 980573356; telephone (425) 2271622; fax (425) 2271149.