[Federal Register: May 23, 2006 (Volume 71, Number 99)]
[Rules and Regulations]
[Page 29578-29580]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23my06-5]
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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]
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