[Federal Register Volume 70, Number 250 (Friday, December 30, 2005)]
[Rules and Regulations]
[Pages 77301-77303]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-24531]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21611; Directorate Identifier 2004-NM-234-AD; 
Amendment 39-14438; AD 2005-26-17]
RIN 2120-AA64


Airworthiness Directives; Airbus 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

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

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A300-600, A310-200, and A310-300 series airplanes. 
This 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 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 AD results from reports 
of debonded skins on the elevators. 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.

DATES: This AD becomes effective February 3, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of February 3, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

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 street address stated in the 
ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Airbus Model 
A300 B4-600, B4-600R, and F4-600R series airplanes; Model A300 C4-605R 
Variant F airplanes (collectively called A300-600 series airplanes); 
and Model A310 series airplanes. That NPRM was published in the Federal 
Register on June 22, 2005 (70 FR 36073). That NPRM proposed to require 
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 corrective 
actions if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.

Request To Clarify Applicability

    The commenter, the airplane manufacturer, requests that we clarify 
the applicability statement of the proposed AD. The proposed AD states 
that the AD would apply to affected models ``equipped with carbon fiber 
elevators having part number (P/N) A55276055000 (left-hand side) or P/N 
A55276056000 (right-hand side).'' The commenter notes that the related 
French airworthiness directive states that it is effective for affected 
models ``equipped with carbon fiber elevators P/N A55276055000 (left-
hand side) and P/N A55276056000 (right-hand side), installed as per 
modification 4805, * * *.'' The commenter asks that we

[[Page 77302]]

revise the applicability statement of the proposed AD to indicate that 
an affected airplane would be equipped with both the left- and right-
hand side P/Ns, and that the proposed AD only applies to airplanes with 
these P/Ns installed in accordance with (Airbus) Modification 4805.
    We partially agree with the commenter's request.
    After the comment period closed, we coordinated with the commenter 
to gain a better understanding of its comments. This coordination 
resulted in agreement between the FAA and the commenter that, because 
carbon fiber elevators are interchangeable among any airplanes with 
Airbus Modification 4805, it is more appropriate for this AD to apply 
to affected models ``equipped with carbon fiber elevators P/N 
A55276055000 (left-hand side) or P/N A55276056000 (right-hand side),'' 
as specified in the NPRM. (The commenter requests that we disregard its 
former objection concerning the use of ``or'' instead of ``and.'') 
Thus, no change is needed in this regard.
    Regarding the commenter's other request, we agree to revise the 
applicability statement to clarify that carbon fiber elevators with the 
affected P/Ns were installed under Airbus Modification 4805.

Explanation of Additional Change to Applicability

    We have revised the applicability of this AD to identify model 
designations as published in the most recent type certificate data 
sheet for the affected models.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing a modification that will 
address the unsafe condition addressed by this AD. Once this 
modification is developed, approved, and available, the FAA may 
consider additional rulemaking.

Costs of Compliance

    This AD will affect about 172 airplanes of U.S. registry.
    The inspection for the serial number will take about 1 work hour 
per airplane, at an average labor rate of $65 per work hour. Based on 
these figures, the estimated cost of this action for U.S. operators is 
$11,180, or $65 per airplane.
    The detailed inspection, visual inspection with a low-angle light, 
and tap-test inspection of the elevator will take about 3 work hours 
per elevator (two elevators per airplane), at an average labor rate of 
$65 per work hour. Based on these figures, the estimated cost of this 
action for U.S. operators is $67,080, or $390 per airplane, per 
inspection cycle.

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2005-26-17 Airbus: Amendment 39-14438. Docket No. FAA-2005-21611; 
Directorate Identifier 2004-NM-234-AD.

Effective Date

    (a) This AD becomes effective February 3, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
B4-622, B4-605R, 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; equipped with 
carbon fiber elevators having part number (P/N) A55276055000 (left-
hand side) or P/N A55276056000 (right-hand side), installed under 
Airbus Modification 04805.

Unsafe Condition

    (d) This AD results from reports of debonded skins on the 
elevators. The FAA is 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.

Inspection for Serial Number, Repetitive Inspections, and Corrective 
Actions

    (f) Within 600 flight hours after the effective date of this AD, 
inspect to

[[Page 77303]]

determine if the serial number (S/N) of the elevator is listed in 
Airbus All Operators Telex (AOT) A300-600-55A6032, dated June 23, 
2004 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, C4-605R Variant F, F4-605R, and F4-622R airplanes); or in 
Airbus AOT A310-55A2033, dated June 23, 2004 (for Model A310-203, -
204, -221, -222, -304, -322, -324, and -325 airplanes).
    (1) If the S/N does not match any S/N on either AOT S/N list, no 
further action is required by this paragraph.
    (2) If the S/N matches a S/N listed in an AOT, 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 at intervals 
not to exceed 600 flight hours. Do applicable corrective actions 
before further flight.

                    Table 1.--Repetitive Inspections
------------------------------------------------------------------------
            Do a--                   Of the--            For any--
------------------------------------------------------------------------
Detailed inspection...........  Elevator upper     Damage (i.e., breaks
                                 and lower          in the graphite
                                 external skin      fiber reinforced
                                 surfaces.          plastic (GFRP)/
                                                    Tedlar film
                                                    protection, debonded
                                                    GFRP/Tedlar film
                                                    protection, bulges,
                                                    torn-out plies).
Visual inspection with a low-   Elevator upper     Differences in the
 angle light.                    and lower          surface reflection.
                                 external skin
                                 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 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).

Parts Installation

    (h) As of the effective date of this AD, 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.

No Reporting Required

    (i) Although the AOTs referenced in this AD specify to submit 
inspection reports to the manufacturer, this AD does not include 
that requirement.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, International Branch, ANM-116, 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 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (k) French airworthiness directive F-2004-131, dated August 4, 
2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use Airbus All Operators Telex A300-600-55A6032, 
dated June 23, 2004; or Airbus All Operators Telex A310-55A2033, 
dated June 23, 2004; as applicable; to perform the actions that are 
required by this AD, unless the AD specifies otherwise. (The 
document number and date are only included on the first page of 
these documents.) The Director of the Federal Register approved the 
incorporation by reference of these documents in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this 
service information. You may review copies at the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street SW., 
Room PL-401, Nassif Building, Washington, DC; on the Internet at 
http://dms.dot.gov; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 15, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-24531 Filed 12-29-05; 8:45 am]
BILLING CODE 4910-13-U