[Federal Register Volume 70, Number 223 (Monday, November 21, 2005)]
[Rules and Regulations]
[Pages 70035-70038]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-22789]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23005; Directorate Identifier 2003-NM-110-AD; 
Amendment 39-14379; AD 2005-23-21]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A340-200 and A340-300 
Series 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 all 
Airbus Model A340-200 and A340-300 series airplanes. This AD requires 
repetitive inspections for cracking of the junction between the thrust 
reverser forward frame and the 12 o'clock and 6 o'clock beams; the 
thrust reverser common fittings; and the thrust reverser J-ring 
structure at the 12 o'clock and 6 o'clock positions; and related 
investigative and corrective actions. This AD results from fatigue and 
damage tolerance testing of the engine thrust reversers which revealed 
fatigue cracking of the junction between the thrust reverser forward 
frame and the 12 o'clock beam, and of the thrust reverser J-ring 
structure. We are issuing this AD to detect and correct such fatigue 
cracking, which could result in rupture of the J-ring, forward frame, 
or common fittings; loss of the thrust reverser system; or inadvertent 
deployment of a thrust reverser in flight and consequent reduced 
controllability of the airplane.

DATES: This AD becomes effective December 6, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of December 6, 
2005.
    We must receive comments on this AD by January 20, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this 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 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France; or Rohr Inc., 850 Lagoon Drive, Chula Vista, California 91912; 
for service information identified in this AD.

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

SUPPLEMENTARY INFORMATION:

Discussion

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on all Airbus Model A340-200 and A340-300 
series airplanes. The DGAC advises that fatigue and damage tolerance 
testing of the engine thrust reversers revealed cracking of the 
junction between the thrust reverser forward frame and the 12 o'clock 
beam. The cracking of the junction was found after the accumulation of 
approximately 20,000 total flight cycles. In addition to the fatigue 
cracking that was found during fatigue tests, fatigue cracking of the 
J-ring was also found on in-service airplanes that had accumulated 
fewer than 6,666 total flight cycles. These conditions, if not 
corrected, could result in rupture of the J-ring, forward frame, or 
common fittings; loss of the thrust reverser system; or inadvertent 
deployment of a thrust reverser in flight

[[Page 70036]]

and consequent reduced controllability of the airplane.

Relevant Service Information

    Airbus has issued Service Bulletin A340-78-4028, including Appendix 
01, Revision 01, dated October 23, 2003. The service bulletin describes 
procedures for repetitive inspections for cracking of the junction 
between the thrust reverser forward frame and the 12 o'clock and 6 
o'clock beams and the thrust reverser common fittings, and related 
investigative and corrective actions.
    The Airbus Service Bulletin refers to Rohr Service Bulletin 
RA34078-71, Revision 1, dated February 7, 2003, as an appropriate 
source of service information for accomplishing the eddy current 
inspections for cracking. The related investigative and corrective 
actions include performing eddy current inspections for missing 
fasteners, installing missing fasteners, replacing the thrust reverser 
with a new thrust reverser if any cracking is found or missing 
fasteners cannot be replaced, and contacting the manufacturer to report 
any damage.
    The DGAC mandated the Airbus service information and issued French 
airworthiness directives 2003-108(B), dated March 19, 2003; and F-2004-
020, dated February 4, 2004, to ensure the continued airworthiness of 
these airplanes in France.
    The parts manufacturer has also issued the following service 
bulletins:

----------------------------------------------------------------------------------------------------------------
                                         Revision
           Service bulletin               level              Date                         Including
----------------------------------------------------------------------------------------------------------------
CFM International CFM56-5C Alert                 2  January 27, 2004......  Rohr Alert Service Bulletin RA340A78-
 Service Bulletin 78-A0072.                                                  72, Revision 2, dated January 27,
                                                                             2004
CFM International CFM56-5C Alert                 1  January 27, 2004......  Rohr Alert Service Bulletin RA340A78-
 Service Bulletin 78-A0073.                                                  73, Revision 1, dated January 27,
                                                                             2004
----------------------------------------------------------------------------------------------------------------

    Service Bulletin 78-A0072 describes procedures for repetitive eddy 
current inspections for cracking of the J-ring structure at the 12 
o'clock and 6 o'clock positions, and corrective action if necessary. 
The corrective action procedures specify replacing the thrust reverser 
with a new thrust reverser. Service Bulletin 78-A0073 describes 
procedures for modifying the J-ring and replacing the 12 o'clock 
fitting (including inspecting machined parts for cracks and contacting 
the manufacturer if necessary.)

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 this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC'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 and correct fatigue 
cracking of the J-ring and on the junction between the forward frame 
and the 12 o'clock beam, which could result in rupture of the J-ring, 
forward frame, or common fittings, inadvertent deployment of a thrust 
reverser in flight and consequent reduced controllability of the 
airplane. This AD requires accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Differences Among This AD, Service Bulletins, and French 
Airworthiness Directives.''

Differences Among This AD, Service Bulletins, and French Airworthiness 
Directives

    French airworthiness directive 2003-108(B) specifies certain 
compliance thresholds for the inspection of the thrust reversers since 
new. For certain airplanes, this AD would require you to perform the 
inspections at those thresholds or within 6 months after the effective 
date of the AD, whichever is latest. We have included a 6-month grace 
period to ensure that any airplane that is close to or has passed the 
threshold is not grounded as of the effective date of the AD.
    If any cracking is found on machined parts during the inspections 
specified in CFM International CFM56-5C Alert Service Bulletin 78-
A0073, and the service bulletin specifies contacting Airbus or CFM for 
repair, this AD requires repairing those conditions using a method that 
we approve.
    If damage is found on any common fitting during the inspections 
specified in Airbus Service Bulletin A340-78-4028, and the service 
bulletin specifies contacting Airbus for repair, this AD requires 
repairing those conditions using a method that we approve.
    Although Airbus Service Bulletin A340-78-4028 and CFM International 
CFM56-5C Alert Service Bulletin 78-A0072, specify reporting the 
replacement of any thrust reverser to Airbus or CFM, this AD does not 
include that requirement.

Clarification of Inspection Terminology

    The French airworthiness directives specify a ``visual inspection'' 
and an ``inspection'' for cracking of the J-ring structure at the 
junction between the forward frame and the 12 o'clock and 6 o'clock 
beams of the engine thrust reversers. We refer to these inspections as 
``detailed inspections.'' We have included the definition for a 
detailed inspection in a note in the AD. (This terminology is 
consistent with the terminology used in the service information.)

Clarification of Optional Replacement

    If a crack is detected at the 12 o'clock fitting, the French 
airworthiness directive F-2004-020 includes replacing the thrust 
reverser as one option for the corrective action.

Costs of Compliance

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes affected by this AD are currently operated by 
non-U.S. operators under foreign registry; therefore, they are not 
directly affected by this AD action. However, we consider this AD 
necessary to ensure that the unsafe condition is addressed if any 
affected airplane is imported and placed on the U.S. Register in the 
future.
    If an affected airplane is imported and placed on the U.S. Register 
in the future, the required actions would take about 2 work hours per 
airplane, at an average labor rate of $65 per work hour. Based on these 
figures, the estimated cost of the AD would be $130 per airplane, per 
inspection cycle.

FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is 
unnecessary before this AD is issued,

[[Page 70037]]

and this AD may be made effective in less than 30 days after it is 
published in the Federal Register.

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-2005-
23005; Directorate Identifier 2003-NM-110-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 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 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.

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.

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):

2005-23-21 Airbus: Amendment 39-14379. Docket No. FAA-2005-23005; 
Directorate Identifier 2003-NM-110-AD.

Effective Date

    (a) This AD becomes effective December 6, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A340-211, -212, and -213 
and A340-311, -312, and -313 airplanes, certificated in any 
category.

Unsafe Condition

    (d) This AD results from fatigue and damage tolerance testing of 
the engine thrust reversers which revealed fatigue cracking of the 
junction between the thrust reverser forward frame and the 12 
o'clock beam, and of the thrust reverser J-ring structure. We are 
issuing this AD to detect and correct such fatigue cracking, which 
could result in rupture of the J-ring, forward frame, or common 
fittings; loss of the thrust reverser system; or inadvertent 
deployment of a thrust reverser in flight and consequent 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.

    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 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Repetitive Inspections/Investigative and Corrective Actions

    (f) Accomplish detailed and eddy current inspections for 
cracking of the junction between the thrust reverser forward frame 
and the 12 o'clock and 6 o'clock beams, and the thrust reverser 
common fittings, and related investigative and corrective actions, 
by doing all the actions in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A340-78-4028, Revision 01, 
dated October 23, 2003. Except, if damage is found on the common 
fittings, repair the damage using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA. 
Do the inspections at the later of the times specified in paragraphs 
(f)(1) and (f)(2) of this AD. Do any related investigative and 
corrective actions before further flight in accordance with the 
service bulletin. Repeat the inspections thereafter at intervals not 
to exceed 4,500 flight cycles on the thrust reverser.
    (1) For thrust reversers that have accumulated fewer than 4,500 
total flight cycles since new as of the effective date of this AD: 
Before the accumulation of 4,500 total flight cycles on the thrust 
reverser since new, or within 2,166 flight cycles after the 
effective date of this AD, whichever is later.
    (2) For thrust reversers that have accumulated 4,500 or more 
total flight cycles since new as of the effective date of this AD: 
Before the accumulation of 6,666 total flight

[[Page 70038]]

cycles on the thrust reverser since new or within 6 months after the 
effective date of this AD, whichever is later.

    Note 2: Airbus Service Bulletin A340-78-4028, Revision 01, dated 
October 23, 2003, references Rohr Service Bulletin RA34078-71, 
Revision 1, dated February 7, 2003, as an additional source of 
service information for accomplishing the applicable actions in 
paragraph (f) of this AD.

    (g) At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Accomplish an eddy current inspection for 
cracking of the J-ring structure at the 12 o'clock and 6 o'clock 
positions by doing all the applicable actions in accordance with CFM 
International CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, 
dated January 27, 2004, including Rohr Alert Service Bulletin 
RA340A78-72, Revision 2, dated January 27, 2004. If no cracking is 
found: Repeat the inspection thereafter at intervals not to exceed 
800 flight hours or 175 flight cycles on the thrust reverser, 
whichever is first.
    (1) Before the accumulation of 3,000 total flight cycles on any 
thrust reverser since new.
    (2) Within 800 flight hours or 175 flight cycles after the 
effective date of this AD, whichever is first.
    (h) If any cracking is found at the 12 o'clock position, before 
further flight, do the actions required by either paragraph (h)(1) 
or (h)(2) of this AD.
    (1) Replace the thrust reverser by doing all the applicable 
actions in accordance with CFM International CFM56-5C Alert Service 
Bulletin 78-A0072, Revision 2, dated January 27, 2004, including 
Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated January 
27, 2004.
    (2) Modify the J-ring and replace the 12 o'clock fitting by 
doing all the applicable actions in accordance with CFM 
International CFM56-5C Alert Service Bulletin 78-A0073, Revision 1, 
dated January 27, 2004, including Rohr Alert Service Bulletin 
RA340A78-73, Revision 1, dated January 27, 2004. Except, if any 
cracking is found on machined parts, repair the damage using a 
method approved by the Manager, International Branch, ANM-116. 
Repeat the inspection of the 6 o'clock position only at the time 
specified in paragraph (g) of this AD.
    (i) If cracking is found at the 6 o'clock position: Before 
further flight, replace the thrust reverser by doing all the 
applicable actions in accordance with CFM International CFM56-5C 
Alert Service Bulletin 78-A0072, Revision 2, dated January 27, 2004, 
including Rohr Alert Service Bulletin RA340A78-72, Revision 2, dated 
January 27, 2004.

No Reporting Required

    (j) Although Airbus Service Bulletin A340-78-4028, Revision 01, 
dated October 23, 2003; and CFM International CFM56-5C Alert Service 
Bulletin 78-A0072, Revision 2, dated January 27, 2004, specify 
reporting the replacement of any thrust reverser to Airbus or CFM, 
this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (k)(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 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

    (l) French airworthiness directives 2003-108(B), dated March 19, 
2003; and F-2004-020, dated February 4, 2004, also address the 
subject of this AD.

Material Incorporated by Reference

    (m) You must use Airbus Service Bulletin A340-78-4028, Revision 
01, excluding Appendix 01, dated October 23, 2003; CFM International 
CFM56-5C Alert Service Bulletin 78-A0072, Revision 2, dated January 
27, 2004, including Rohr Alert Service Bulletin RA340A78-72, 
Revision 2, dated January 27, 2004; and CFM International CFM56-5C 
Alert Service Bulletin 78-A0073, Revision 1, dated January 27, 2004, 
including Rohr Alert Service Bulletin RA340A78-73, Revision 1, dated 
January 27, 2004; as applicable; to perform the actions that are 
required by this AD, unless the AD specifies otherwise. 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; or Rohr Inc., 850 Lagoon Drive, Chula Vista, 
California 91912, 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 November 9, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-22789 Filed 11-18-05; 8:45 am]
BILLING CODE 4910-13-P