AD 2006-07-13

[Federal Register Volume 71, Number 61 (Thursday, March 30, 2006)]
[Rules and Regulations]
[Pages 16030-16033]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 06-3119]



[[Page 16030]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24288; Directorate Identifier 2006-NM-068-AD; 
Amendment 39-14540; AD 2006-07-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Airplanes, Model A300 
B4-600 Series Airplanes, Model A300 B4-600R Series Airplanes, Model 
A300 F4-600R Series Airplanes, and Model A300 C4-605R Variant F 
Airplanes

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

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A310 airplanes, Model A300 B4-600 series 
airplanes, Model A300 B4-600R series airplanes, Model A300 F4-600R 
series airplanes, and Model A300 C4-605R Variant F airplanes. This AD 
requires inspections of the rudder for discrepancies and corrective 
action if necessary. This AD also requires reporting all inspection 
results to the airplane manufacturer and the FAA. This AD results from 
two separate findings of inner skin disbonding discovered while 
undergoing unrelated repair and maintenance procedures. We are issuing 
this AD to detect discrepancies of the rudder, which could result in 
reduced structural integrity of the rudder.

DATES: This AD becomes effective March 30, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 30, 
2006.
    We must receive comments on this AD by May 30, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
    <bullet> DOT Docket Web site: Go to <a href="http://dms.dot.gov">http://dms.dot.gov</a> and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 
a.m. and 5 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 AD.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA) notified us that an 
unsafe condition may exist on certain Airbus Model A310 airplanes; and 
Model A300 B4-600, B4-600R, and F4-600R series airplanes and Model C4-
605R Variant F airplanes (collectively called A300-600 series 
airplanes); equipped with a carbon fiber reinforced plastic (CFRP) 
rudder, any series of part number (P/N) A55471500. The EASA advises 
that, during maintenance on a Model A300-600 series airplane, a CFRP 
rudder was damaged at the trailing edge during a rudder swing test. 
During damage assessment following this event, unrelated disbonding of 
the inner skin to the honeycomb core was detected at the lower skin, 
close to the front spar. Further examination revealed traces of 
hydraulic fluid in the disbonded area. During an inspection performed 
as part of the repair process, damage was found on the inner skin 
starting at the junction between the rudder spar and the lower rib. The 
EASA also advises that, in a separate incident, disbonding of the 
rudder inner skin also was detected on a Model A310 airplane undergoing 
paint removal. Discrepancies of the rudder, if not detected, could 
result in reduced structural integrity of the rudder.

Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A310-55A2043 and AOT 
A300-55A6042, both dated March 2, 2006. The AOTs describe doing the 
following procedures:
    <bullet> Checking the drainage at the lower edge of the rudder spar 
for the correct condition. If the aft edge sides of the leading edge 
butt strap at rib 0 are not clean, the AOTs specify restoring the 
drainage to the correct condition.
    <bullet> Doing a visual examination of the rudder external surfaces 
for the presence of contaminant hydraulic fluids. If any contaminant 
hydraulic fluid is found, the AOTs specify cleaning the rudder external 
surfaces.
    <bullet> Cleaning the inner surface of the rudder panels.
    <bullet> Doing a manual tap test inspection, or an automatic tap 
test inspection using Woodpecker tool WP632, at the inner side of the 
rudder panels for any disbond. If any disbond is found using the manual 
tap test, the AOTs recommend doing a confirmation test using Woodpecker 
tool WP632 of the disbond. If any disbond is found using Woodpecker 
tool WP632, the AOTs specify marking the perimeter of any damaged area 
and documenting the location and size of the finding.
    <bullet> Depending on the number of disbonds found and size of a 
disbond found, the AOTs specify taking the following corrective 
actions: Reinspecting the damaged area or doing a permanent repair, 
within 2,500 flight cycles; doing a permanent repair before further 
flight, or doing a temporary repair before further flight and then the 
permanent repair within 1,500 flight cycles; contacting the 
manufacturer for further instructions before further flight; or 
extending the inspection area to find all the damage.
    <bullet> Reporting all inspection findings to the manufacturer.
    The EASA mandated the AOTs and issued airworthiness directive 2006-
0066, dated March 24, 2006, to ensure the continued airworthiness of 
these airplanes in the European Union.
    AOT A310-55A2043 refers to Chapter 55-42-11 of the Airbus A310 
Structural Repair Manual (SRM) as an additional source of service 
information for restoring the drainage to the correct condition. AOT 
A310-55A2043 refers to Chapter 51-78-20 of the A310 SRM as an 
additional source of service information for cleaning hydraulic fluids 
from the rudder external surfaces. AOT A310-55A2043 refers to Chapter 
55-41-12 of the A310 SRM as an additional source of service information 
for accomplishing the temporary or permanent repair.
    AOT A300-55A6042 refers to Chapter 55-42-11 of the Airbus A300-600 
SRM as an additional source of service information for restoring the 
drainage to the correct condition. AOT A300-55A6042 refers to Chapter 
51-78-20 of the A300-600 SRM as an additional source of service 
information for cleaning hydraulic fluids from the rudder external 
surfaces. AOT A300-55A6042 refers to Chapter 55-41-12 of the A300-600 
SRM as an additional source of service information for accomplishing 
the temporary or permanent repair.

[[Page 16031]]

FAA's Determination and Requirements of This AD

    These airplane models are manufactured in France and are 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. Pursuant to 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 we need to issue an AD for 
products of this type design that are certificated for operation in the 
United States.
    Therefore, we are issuing this AD to detect discrepancies of the 
rudder, which could result in reduced structural integrity of the 
rudder. This AD requires accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Differences Between the AD and the EASA's Airworthiness Directive.'' 
The AD also requires sending all inspection results to Airbus and the 
FAA.

Differences Between the AD and the EASA's Airworthiness Directive

    The EASA's airworthiness directive 2006-0066 requires accomplishing 
any corrective actions in accordance with AOT A310-55A2043 and AOT 
A300-55A6042, as applicable. For the condition where one disbond area 
per panel with a diameter of less than 130mm is found, the AOTs 
recommend either reinspecting or doing a permanent repair within 2,500 
flight cycles after the inspection. However, we have determined that 
the safety of the fleet would be better addressed by repair of the 
damaged area. This AD requires accomplishing either a temporary or 
permanent repair within 6 months. If the temporary repair is 
accomplished, this AD further requires accomplishing the permanent 
repair within 1,500 flight cycles after the temporary repair.
    The EASA's airworthiness directive 2006-0066 describes procedures 
for submitting all inspection results to the manufacturer. This AD also 
requires that action, as well as submitting all inspection findings to 
the FAA.
    The EASA's airworthiness directive 2006-0066 (in accordance with 
the referenced Airbus AOTs) requires contacting the manufacturer for 
instructions on how to repair certain conditions. This AD requires 
repairing those conditions using a method that we approve.

Clarification of Inspection Terminology

    The ``check'' and ``visual examination'' specified in the Airbus 
AOTs are referred to as ``general visual inspections'' in this AD. We 
have included the definition for a general visual inspection in a note 
in this AD.

Interim Action

    This is considered to be interim action. The inspection reports 
that are required by this AD will enable the manufacturer to obtain 
better insight into the nature, cause, and extent of the damage, and 
eventually to develop final action to address the unsafe condition. 
Once final action has been identified, the FAA may consider further 
rulemaking.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and good cause exists to make 
this AD effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
24288; Directorate Identifier 2006-NM-068-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to <a href="http://dms.dot.gov">http://dms.dot.gov</a>, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this 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 
<a href="http://dms.dot.gov">http://dms.dot.gov</a>.

Examining the Docket

    You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>, 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.

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 the 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 AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

[[Page 16032]]

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):

2006-07-13 Airbus: Amendment 39-14540. Docket No. FAA-2006-24288; 
Directorate Identifier 2006-NM-068-AD.

Effective Date

    (a) This AD becomes effective March 30, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310 airplanes; Model A300 
B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and 
B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and 
Model A300 C4-605R Variant F airplanes; certificated in any 
category; equipped with a carbon fiber reinforced plastic (CFRP) 
rudder having any series of part number (P/N) A55471500; except for 
those airplanes on which Airbus Modification 8827 has been 
incorporated in production.

Unsafe Condition

    (d) This AD results from two separate findings of inner skin 
disbonding discovered while undergoing unrelated repair and 
maintenance procedures. We are issuing this AD to detect 
discrepancies of the rudder, which could result in reduced 
structural integrity of the rudder.

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.

Inspections and Corrective Actions

    (f) Within 500 flight cycles or 120 days after the effective 
date of this AD, whichever occurs first: Do the actions specified in 
paragraphs (f)(1), (f)(2), and (f)(3) of this AD, in accordance with 
paragraph 4.2.2 of Airbus All Operators Telex (AOT) A310-55A2043 
(for Model A310 airplanes) or AOT A300-55A6042 (for Model A300 B4-
601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and 
B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and 
Model A300 C4-605R Variant F airplanes), both dated March 2, 2006, 
as applicable.
    (1) Do a general visual inspection of the drainage at the lower 
edge of the rudder spar to determine if the aft edges of the leading 
edge butt strap at rib 0 are clean. If any aft edge side of the 
leading edge butt strap at rib 0 is not clean, before further 
flight, restore the drainage to the correct condition.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''


    Note 2: AOT A310-55A2043 refers to Chapter 55-42-11 of the 
Airbus A310 Structural Repair Manual (SRM) as an additional source 
of service information for restoring the drainage to the correct 
condition. AOT A300-55A6042 refers to Chapter 55-42-11 of the Airbus 
A300-600 SRM as an additional source of service information for 
restoring the drainage to the correct condition.

    (2) Do a general visual inspection of the rear spar of the 
rudder external surfaces below the rudder actuators for the presence 
of hydraulic fluid. If any hydraulic fluid is found, before further 
flight, clean the contaminated rudder external surfaces.

    Note 3: AOT A310-55A2043 refers to Chapter 51-78-20 of the 
Airbus A310 SRM as an additional source of service information for 
cleaning hydraulic fluids from the rudder external surfaces. AOT 
A300-55A6042 refers to Chapter 51-78-20 of the Airbus A300-600 SRM 
as an additional source of service information for cleaning 
hydraulic fluids from the rudder external surfaces.

    (3) Clean the inner surface of the rudder panels and do a manual 
tap test inspection, or an automatic tap test inspection using 
Woodpecker tool WP632, at the inner side of the rudder panels for 
any disbonding in the inspection areas defined in Airbus Technical 
Disposition 943.0046/06, dated March 2, 2006. If any disbond area is 
found during a manual tap test inspection, as an option, an 
automatic tap test inspection using Woodpecker tool WP632 may be 
accomplished before further flight to verify the finding. If any 
disbond area crosses the perimeter of any inspection zone defined in 
Airbus Technical Disposition 943.0046/06, before further flight, 
repeat the tap test inspection in the applicable area outside of the 
defined inspection zone to obtain the size of the entire disbond 
area.
    (i) If one disbond area per panel with a diameter of less than 
130mm is found during the inspection required by paragraph (f)(3) of 
this AD: Within 6 months, do a temporary or permanent repair of the 
disbond area using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA. Chapter 55-41-
12 of the Airbus A310 SRM is one approved method for accomplishing 
the temporary or permanent repair on Model A310 airplanes. Chapter 
55-41-12 of the Airbus A300-600 SRM is one approved method for 
accomplishing the temporary or permanent repair on Model A300 B4-
601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and 
B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and 
Model A300 C4-605R Variant F airplanes. If a temporary repair is 
accomplished, within 1,500 flight cycles after accomplishing the 
temporary repair, do a permanent repair of the disbond area in 
accordance with this paragraph.
    (ii) If one disbond area per panel with a diameter of 130mm or 
greater, but less than 200mm, is found during the inspection 
required by paragraph (f)(3) of this AD: Before further flight after 
the inspection, do a temporary or permanent repair of the disbond 
area using a method approved by the Manager, International Branch, 
ANM-116, FAA. Chapter 55-41-12 of the Airbus A310 SRM is one 
approved method for accomplishing the temporary or permanent repair 
on Model A310 airplanes. Chapter 55-41-12 of the Airbus A300-600 SRM 
is one approved method for accomplishing the temporary or permanent 
repair on Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; 
Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-
622R airplanes; and Model A300 C4-605R Variant F airplanes. If a 
temporary repair is accomplished, within 1,500 flight cycles after 
accomplishing the temporary repair, do a permanent repair of the 
disbond area in accordance with this paragraph.
    (iii) If one disbond area per panel with a diameter of 200mm or 
greater is found during the inspection required by paragraph (f)(3) 
of this AD: Before further flight after the inspection, repair the 
disbond area using a method approved by the Manager, International 
Branch, ANM-116, FAA.
    (iv) If more than one disbond area of any diameter is found on a 
single panel during the inspection required by paragraph (f)(3) of 
this AD: Before further flight, repair the disbond areas using a 
method approved by the Manager, International Branch, ANM-116, FAA.

Reporting Requirement

    (g) At the applicable time specified in paragraph (g)(1) or 
(g)(2) of this AD, submit a report of all findings (both positive 
and negative) of the inspection required by paragraph (f)(3) of this 
AD to M. Xavier Jolivet, Dept. SEE83; fax +33(0) 5 61-93-36-14; e-
mail <a href="/cdn-cgi/l/email-protection#b9e1d8cfd0dccb97f3d6d5d0cfdccdf9d8d0cbdbccca97dad6d4"><span class="__cf_email__" data-cfemail="b8e0d9ced1ddca96f2d7d4d1ceddccf8d9d1cadacdcb96dbd7d5">[email&#160;protected]</span></a>, and to Thomas Stafford, 
International Branch, ANM-116, FAA; fax (425) 227-1149; e-mail 
<a href="/cdn-cgi/l/email-protection#81d5e9eeece0f2afd2f5e0e7e7eef3e5c1e7e0e0afe6eef7"><span class="__cf_email__" data-cfemail="1b4f7374767a6835486f7a7d7d74697f5b7d7a7a357c746d">[email&#160;protected]</span></a>. The report must include the inspection 
results, a description of any discrepancies found, the airplane 
serial number, and the number of landings and flight hours on the 
airplane. Under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has

[[Page 16033]]

approved the information collection requirements contained in this 
AD and has assigned OMB Control Number 2120-0056.
    (1) If the inspection is accomplished after the effective date 
of this AD: Submit the report within 10 days after the inspection.
    (2) If the inspection was accomplished before the effective date 
of this AD: Submit the report within 10 days after the effective 
date of this AD.

Parts Installation

    (h) As of the effective date of this AD, no person may install a 
CFRP rudder, any series of P/N A55471500, on any airplane, unless 
the CFRP rudder has been inspected and any applicable corrective 
action has been accomplished in accordance with paragraphs (f)(2) 
and (f)(3) of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, International Branch, ANM-116, 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.

Related Information

    (j) The European Aviation Safety Agency's airworthiness 
directive 2006-0066, dated March 24, 2006, also addresses the 
subject of this AD.

Material Incorporated by Reference

    (k) You must use Airbus All Operators Telex A310-55A2043, dated 
March 2, 2006, or Airbus All Operators Telex A300-55A6042, dated 
March 2, 2006, as applicable; and Airbus Technical Disposition 
943.0046/06, dated March 2, 2006; to perform the actions that are 
required by this AD, unless the AD specifies otherwise. (Only page 1 
of Airbus All Operators Telex A310-55A2043 and Airbus All Operators 
Telex A300-55A6042 contains the document number and date of the 
document; no other page of the document contains this information.) 
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 <a href="http://dms.dot.gov">http://dms.dot.gov</a>; 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 <a href="http://www.archives.gov/">http://www.archives.gov/</a> 
federal--register/code--of--federal--regulations/ ibr--
locations.html.

    Issued in Renton, Washington, on March 24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-3119 Filed 3-28-06; 12:45 pm]
BILLING CODE 4910-13-P