[Federal Register Volume 71, Number 99 (Tuesday, May 23, 2006)]
[Rules and Regulations]
[Pages 29578-29580]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-4712]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24815; Directorate Identifier 2006-NM-101-AD; 
Amendment 39-14608; AD 2006-11-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318, A319, A320, and A321 
Airplanes

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to certain Airbus Model A319, A320, and A321 
airplanes. The existing AD currently requires a one-time ultrasonic 
inspection for certain airplanes, and repetitive detailed inspections 
for all airplanes, for cracking in the forward lug of the support rib 5 
fitting of both main landing gear (MLG), and repair if necessary. The 
existing AD also provides for optional terminating actions. This AD 
removes the requirement for the one-time ultrasonic inspection and 
reduces the compliance time and repetitive interval for the detailed 
inspection of all airplanes. This AD also adds certain Airbus Model 
A318 airplanes to the applicability. This AD continues to provide 
optional terminating action for certain airplanes, as well as other 
optional methods of complying with the AD's requirements. This AD 
results from a new crack that was found in the forward lug of the MLG 
support rib 5 fitting. We are issuing this AD to detect and correct 
cracking in the forward lug of the MLG, which could result in failure 
of the lug and consequent collapse of the MLG during takeoff or 
landing.

DATES: This AD becomes effective June 7, 2006.
    We must receive any comments on this AD by July 24, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     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.
    You may examine the contents of 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., Room PL-
401, on the plaza level of the Nassif Building, Washington, DC. This 
docket number is FAA-2006-24815; the directorate identifier for this 
docket is 2006-NM-101-AD.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    On June 6, 2005, the FAA issued AD 2005-12-07, amendment 39-14123 
(70 FR 39559, July 8, 2005). That AD applies to certain Airbus Model 
A319, A320, and A321 series airplanes. That AD requires a one-time 
ultrasonic inspection for certain airplanes, and repetitive detailed 
inspections for all airplanes, for cracking in the forward lug of the 
support rib 5 fitting of both main landing gear (MLG), and repair if 
necessary. That AD also provides for optional terminating actions. That 
AD resulted from a report of a crack found in the forward lug of the 
right-hand MLG rib 5 fitting during greasing of both MLG pintle 
bearings. The actions specified in that AD are intended to find and fix 
cracking in the forward lug of the MLG, which could result in failure 
of the lug and consequent collapse of the MLG during landing.

Actions Since AD Was Issued

    Since we issued that AD, a new crack was found in the forward lug 
of a MLG support rib, the same area subject to inspection under AD 
2005-12-07. Investigation revealed the need to reduce the inspection 
threshold and repetitive interval of the detailed inspection currently 
required by the existing AD. It has also been determined that the 
ultrasonic inspection required by the existing AD for certain airplanes 
is no longer necessary because of the reduced threshold for the 
detailed inspection.
    It has been determined that certain Airbus Model A318 airplanes 
should be subject to the same inspections required for Model A319, 
A320, and A321 airplanes by AD 2005-12-07.
    The European Aviation Safety Agency (EASA) issued emergency 
airworthiness directive 2006-0069R1, dated April 7, 2006, to ensure the 
continued airworthiness of these airplanes in the European Union.

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. 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

[[Page 29579]]

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 supersede AD 2005-12-07. This 
new AD continues to require repetitive detailed inspections for 
cracking in the forward lug of the support rib 5 fitting of both MLG at 
a reduced compliance time and repetitive interval. Inspections must be 
done in accordance with a method approved by the FAA or the EASA. 
Inspecting in accordance with Airbus A318/A319/A320/A321 Nondestructive 
Testing Manual (NTM) Chapter 51-90-00, revision dated February 1, 2003, 
is one approved method for performing the detailed inspections. If any 
cracking is found, this AD requires replacing the MLG fitting with a 
new fitting in accordance with a method approved by the FAA or the 
EASA.
    This AD also provides for the following optional actions:
     Performing an ultrasonic inspection for cracking in the 
forward lug of the support rib 5 fitting of both MLG in accordance with 
a method approved by the FAA or the EASA, as an acceptable method of 
complying with this AD's inspection requirements. Doing the ultrasonic 
inspection in accordance with Airbus A318/A319/A320/A321 NTM Chapter 
57-29-03, revision dated February 1, 2005 (for Airbus Model A318, A319, 
and A320 airplanes), or Chapter 57-29-04, revision dated May 1, 2005 
(for Airbus Model A321 airplanes), as applicable, is one approved 
method for doing this ultrasonic inspection.
     For Airbus A319, A320, and A321 airplanes: Accomplishing 
optional terminating action in accordance with Airbus Service Bulletin 
A320-57-1118, dated September 5, 2002; or Revision 01, dated August 28, 
2003.
     For Airbus A319, A320, and A321 airplanes: Repairing the 
forward lugs of the support rib 5 fitting of both MLG in accordance 
with a method approved by the FAA or the EASA, as an optional 
terminating action. Repairing in accordance with Airbus A319 Structural 
Repair Manual (SRM) Chapter 5.C., 57-26-13, or Airbus A320 SRM Chapter 
5.D., 57-26-13, revisions dated November 1, 2004; or Airbus A321 SRM 
Chapter 5.D., 57-26-13, revision dated February 1, 2005; as applicable; 
is one approved method for doing this repair.

Differences Between the EASA's Emergency Airworthiness Directive and 
This AD

    EASA's emergency airworthiness directive specifies that, if cracks 
are found, you must contact the manufacturer for instructions on 
replacing the MLG fitting before the next flight. However, this AD 
requires you to replace the MLG fitting in accordance with a method 
that we or the EASA (or its delegated agent) approve.
    The EASA's emergency airworthiness directive permits further flight 
if a crack finding occurs but no crack is visible during accomplishment 
of the ultrasonic inspection (which is an optional method of complying 
with the inspection requirements of this AD). However, this AD does not 
permit further flight if there is a crack or a crack finding. We have 
determined that, because of the safety implications and consequences 
associated with cracking in the subject area, the MLG fitting must be 
replaced with a new fitting before further flight.
    These differences have been coordinated with the EASA.

Clarification of Inspection Terminology

    In this AD, the ``detailed visual inspection'' specified in the 
EASA's airworthiness directive is referred to as a ``detailed 
inspection.'' We have included the definition for a detailed inspection 
in a note in the AD.

Interim Action

    We consider this AD interim action. We are currently considering 
requiring the optional modification of the lugs of the support rib 5 
fitting of both MLG, which would constitute terminating action for the 
repetitive inspections required by this AD action. However, the planned 
compliance time for the modification would require us to provide notice 
and opportunity for prior public comment on the merits of the 
modification.

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-
24815; Directorate Identifier 2006-NM-101-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 can review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78), or you can 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.

[[Page 29580]]

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, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends part 39 of the Federal Aviation Regulations (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 
removing amendment 39-14123 (70 FR 39559, July 8, 2005) and adding the 
following new AD:

2006-11-04 Airbus: Docket No. FAA-2006-24815; Directorate Identifier 
2006-NM-101-AD; Amendment 39-14608.

Effective Date

    (a) This AD becomes effective June 7, 2006.

Affected ADs

    (b) This AD supersedes AD 2005-12-07.

Applicability

    (c) This AD applies to Airbus Model A318, A319, A320, and A321 
airplanes, certificated in any category; except those on which 
Airbus Modification 32025 was done during production.

Unsafe Condition

    (d) This AD results from a new crack that was found in the 
forward lug of the MLG support rib 5 fitting. We are issuing this AD 
to detect and correct cracking in the forward lug of the MLG, which 
could result in failure of the lug and consequent collapse of the 
MLG during takeoff or landing.

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.

Repetitive Detailed Inspections

    (f) Within 8 days after the effective date of this AD, or before 
further flight after a hard landing, whichever is first: Perform a 
detailed inspection for cracking in the forward lug of the support 
rib 5 fitting of the left- and right-hand MLG, and, if any crack is 
found, replace the MLG fitting with a new fitting before further 
flight, in accordance with a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA) (or its delegated 
agent). Accomplishing the actions specified in the Airbus A318/A319/
A320/A321 Nondestructive Testing Manual, Chapter 51-90-00, revision 
dated February 1, 2003, is one approved method for performing the 
detailed inspection. Repeat the inspection thereafter at intervals 
not to exceed 8 days, or before further flight after a hard landing, 
whichever is first.

    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.''

Optional Inspection Method

    (g) Performing an ultrasonic inspection for cracking in the 
forward lug of the support rib 5 fitting of the left- and right-hand 
MLG in accordance with a method approved by the Manager, 
International Branch, ANM-116, or the EASA (or its delegated agent), 
is an acceptable alternative method of compliance for the initial 
and repeat inspections required by paragraph (f) of this AD. Doing 
the actions specified in the Airbus A318/A319/A320/A321 
Nondestructive Testing Manual, Chapter 57-29-03, revision dated 
February 1, 2005 (for Airbus Model A318, A319, and A320 airplanes), 
or Chapter 57-29-04, revision dated May 1, 2005 (for Airbus Model 
A321 airplanes), as applicable, is one approved method for 
performing the ultrasonic inspection.

Optional Terminating Action

    (h) For Model A319, A320, and A321 airplanes; as identified in 
Airbus Service Bulletin A320-57-1118, dated September 5, 2002; or 
Revision 01, dated August 28, 2003: Modifying the lugs of the 
support rib 5 fitting of the left- and right-hand MLG and 
accomplishing all related investigative actions and all applicable 
corrective actions in accordance with Airbus Service Bulletin A320-
57-1118, or Revision 01, constitutes terminating action for the 
requirements of this AD.
    (i) For Model A319, A320, and A321 airplanes: Repair of the 
forward lugs of the support rib 5 fitting of the left- and right-
hand MLG in accordance with a method approved by the Manager, 
International Branch, ANM-116, or the EASA (or its delegated agent), 
constitutes terminating action for the requirements of this AD. 
Doing the repair in accordance with Airbus A319 Structural Repair 
Manual Chapter 5.C., 57-26-13, or Airbus A320 Structural Repair 
Manual Chapter 5.D., 57-26-13; revisions dated November 1, 2004; or 
Airbus A321 Structural Repair Manual, Chapter 5.D., 57-26-13, 
revision dated February 1, 2005; as applicable; is one approved 
method.

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 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

    (k) EASA emergency airworthiness directive 2006-0069R1, dated 
April 7, 2006, also addresses the subject of this AD.

Material Incorporated by Reference

    (l) None.

    Issued in Renton, Washington, on May 15, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-4712 Filed 5-22-06; 8:45 am]
BILLING CODE 4910-13-P