[Federal Register Volume 72, Number 94 (Wednesday, May 16, 2007)]
[Proposed Rules]
[Pages 27493-27497]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-9391]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28159; Directorate Identifier 2006-NM-257-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600 Series Airplanes 
and Model A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model A300-600, A310-200, 
and A310-300 series airplanes. The existing 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 proposed AD would also require inspecting 
for damage of the identified elevators in accordance with a new 
repetitive inspection program, at new repetitive intervals; and would 
provide

[[Page 27494]]

an optional terminating action for the repetitive inspections. This 
proposed AD results from reports of damage caused by moisture/water 
inside the elevator. We are proposing 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.

DATES: We must receive comments on this proposed AD by June 15, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9:00 
a.m. and 5:00 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2007-28159; Directorate Identifier 2006-NM-257-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    On December 15, 2005, we issued AD 2005-26-17, amendment 39-14438 
(70 FR 77301, December 30, 2005), for certain Airbus Model A300-600, 
A310-200, and A310-300 series airplanes. That AD 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 
GFRP (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. That AD resulted from reports of 
debonded skins on the elevators. We issued that 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.

Actions Since Existing AD Was Issued

    The preamble to AD 2005-26-17 specified that we considered the 
requirements ``interim action'' and that the manufacturer was 
developing a modification to address the unsafe condition. That AD 
explained that we may consider further rulemaking if a modification is 
developed, approved, and available. The manufacturer now has developed 
such a modification, and we have determined that further rulemaking is 
indeed necessary; this proposed AD follows from that determination.
    In addition, the European Aviation Safety Agency (EASA), which is 
the Technical Agent for the Member States of the European Union, has 
issued EASA airworthiness directive 2006-0289, dated November 2, 2006, 
which renders mandatory a new scheduled inspection program to address 
the unsafe condition.

Relevant Service Information

    Airbus has issued Service Bulletin A300-55-6039 (for Model A300-600 
series airplanes) and Service Bulletin A310-55-2040 (for Model A310 
series airplanes), both including Appendix 01, both dated June 7, 2006. 
The service bulletins describe procedures for determining the serial 
number of the elevator. For elevators with an affected serial number, 
the service bulletins describe procedures for the following actions:
    <bullet> A repetitive detailed visual inspection of the external 
surfaces of the GRFP/Tedlar film protection on the upper and lower skin 
panels to detect damage (breaks, disbonding, bulges, cracks, plies torn 
out or peeled off, discontinuity) of the film. For any damage, the 
service bulletins specify the related investigative action of a local 
tap-test for disbonding of the bulge and the surrounding area. The 
service bulletins specify the corrective action for disbonding as 
removing any disbonded GFRP/Tedlar film before doing the thermographic 
inspection.
    <bullet> A repetitive thermographic inspection of the upper and 
lower skin panels to detect any potential water indication inside the 
panel's honeycomb core; and related investigative and corrective 
actions if necessary.
    <bullet> Related investigative and corrective actions following the 
thermographic inspection are:
    [cir] For no water indication: Evaluation of the external GFRP/
Tedlar film protection for damage (debonding, bulges, cracks, or plies 
torn out or peeled off), and repair with pore filler if necessary.
    [cir] For water indication: A tap-test on the area to detect damage 
and honeycomb debonding; do a damage and repair evaluation according to 
instructions in the structural repair manual (SRM); evaluation of the 
external GFRP/Tedlar film for damage according to the SRM; and repair 
with pore filler and/or replacement of the honeycomb core if necessary, 
or the optional terminating action (described

[[Page 27495]]

below). If any damage exceeds certain limits specified in the SRM, the 
service bulletins specify contacting Airbus for repair instructions.
    <bullet> Reporting inspection results to Airbus.
    <bullet> Repairing the external GFRP/Tedlar film with pore filler.
    Airbus has also issued Service Bulletin A300-55-6040 (for Model 
A300-600 series airplanes) and Service Bulletin A310-55-2041 (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 2005-26-17 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 2005-26-17).
Repetitive inspections (required  3.................  0.................  $240, per           $34,080, per
 by AD 2005-26-17).                                                        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).
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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

[[Page 27496]]

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 39--AIRWORTHINESS 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 39-14438 (70 FR 77301, December 30, 2005) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2007-28159; Directorate Identifier 2006-NM-
257-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by June 15, 
2007.

Affected ADs

    (b) This AD supersedes AD 2005-26-17.

Applicability

    (c) 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.

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 2005-26-17

Inspection for Serial Number, Repetitive Inspections, and 
Corrective Actions

    (f) 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.

                    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,
                                                     torn-out plies).
Visual inspection with a low- Elevator upper and    Differences in the
 angle light.                  lower external skin   surface reflection.
                               surfaces.
Tap-test 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, ANM-116, 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 (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.

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

[[Page 27497]]

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 A300-55-6039 (for Model A300-600 
series airplanes), or 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, 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 A300-55-6039, or 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 accomplished prior to the effective 
date of this AD: Submit the report within 30 days after the 
effective date of this AD.

Optional Terminating Action

    (m) 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 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 
Service Bulletins A310-55-2040 and A300-55-6039, both dated June 7, 
2006.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) Alternative methods of compliance, approved previously in 
accordance with AD 2005-26-17, are approved as alternative methods 
of compliance with the corresponding provisions of this AD.

Related Information

    (o) EASA airworthiness directive 2006-0289, dated November 2, 
2006, also addresses the subject of this AD.

    Issued in Renton, Washington, on May 7, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-9391 Filed 5-15-07; 8:45 am]
BILLING CODE 4910-13-P