[Federal Register: January 14, 2008 (Volume 73, Number 9)]
[Proposed Rules]
[Page 2200-2204]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14ja08-20]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0014; Directorate Identifier 2007-NM-249-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320, and A321
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 2201]]
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Airbus Model A318, A319, A320,
and A321 airplanes. The existing AD currently requires repetitive
inspections 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 optional terminating actions for certain
airplanes, as well as other optional methods for complying with the
inspection requirements of the existing AD. This proposed AD would
continue to require repetitive inspections for cracking in the forward
lug of the support rib 5 fitting of the left and right MLG at new
repetitive intervals in accordance with new service information, and
repair or replacement of any cracked MLG fitting if necessary. This
proposed AD would also require modification of the rib bushings of the
left and right MLG, which would end the repetitive inspections. This
proposed AD results from cracks found in the forward lug of the MLG
support rib 5 fitting. We are proposing this AD to prevent 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: We must receive comments on this proposed AD by February 13,
2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov.
Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0014;
Directorate Identifier 2007-NM-249-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On May 15, 2006, we issued AD 2006-11-04, amendment 39-14608 (71 FR
29578, May 23, 2006), for certain Airbus Model A318, A319, A320, and
A321 airplanes. AD 2006-11-04 requires repetitive detailed inspections
for cracking in the forward lug of the support rib 5 fitting of both
main landing gear (MLG), and repair if necessary. AD 2006-11-04 also
provides optional terminating actions for certain airplanes, as well as
other optional methods for complying with the inspection requirements
of the existing AD. That AD resulted from a new crack that was found in
the forward lug of the MLG support rib 5 fitting. We issued that 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.
Actions Since Existing AD Was Issued
Since we issued AD 2006-11-04, the European Aviation Safety Agency
(EASA), which is the technical agent for the Member States of the
European Union, notified us that the repetitive inspection intervals
must be adjusted and that the optional terminating action, which would
end the repetitive inspections, must be mandated for all airplanes. In
the preamble to AD 2006-11-04, we indicated that the actions required
by that AD were considered ``interim action,'' and that we were
considering further rulemaking to require the modification of the lugs
of the support rib 5 fitting of both MLG, which would terminate the
repetitive inspections required by AD 2006-11-04. We have now
determined that further rulemaking action is indeed necessary, and this
proposed AD follows from that determination.
Relevant Service Information
Airbus has issued Service Bulletin A320-57-1138, Revision 01, dated
October 27, 2006. The service bulletin describes procedures for (1)
doing repetitive visual inspections or repetitive ultrasonic
inspections for cracking in the forward lug of the support rib 5
fitting of the left and right MLG, (2) doing repetitive visual
inspections for cracking in the forward lug of the support rib 5
fitting if any cracking is found during an ultrasonic inspection, and
(3) contacting the manufacturer for instructions if any cracking is
found during a visual inspection. The service bulletin also specifies
that accomplishing Airbus Service Bulletin A320-57-1118 eliminates the
need for the repetitive inspections.
Airbus has also issued Service Bulletin A320-57-1118, Revision 03,
dated April 23, 2007. The service bulletin describes procedures for
modifying the rib bushings of the left and right MLG. The modification
includes removing the existing bushings, doing a visual inspection for
corrosion and damage to the bores and spotfaces, repairing any
corrosion or damage found during the detailed inspection, and
installing new improved bushings and applying a certain protective
sealant to the bores and spotfaces of the lugs for the pintle-pin
bushings of gear rib 5. Accomplishing the modification eliminates the
need for the repetitive inspections specified in Airbus Service
Bulletin A320-57-1138.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The EASA mandated
the service information and issued airworthiness directive 2007-0213,
dated August 7, 2007, to ensure the continued airworthiness of these
airplanes in the European Union.
[[Page 2202]]
FAA's Determination and Requirements of the Proposed AD
These airplanes 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 findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 2006-11-04 and would retain the
requirements of the existing AD, until the new inspections have been
initiated. This proposed AD would also require accomplishing the
actions specified in service information described previously, except
as discussed under ``Differences between Proposed AD and Service
Bulletin.''
Differences Between Proposed AD and Service Bulletin
Although EASA airworthiness directive 2007-0213 specifies repeating
the inspections at the intervals defined in Airbus Service Bulletin
A320-57-1138, the intent is to require the repetitive inspections at
those intervals, or before further flight after a hard landing,
whichever is first. We have coordinated this difference with the EASA.
EASA airworthiness directive 2007-0213 and Airbus Service Bulletin
A320-57-1138 permit further flight if cracking is found during the
ultrasonic inspection but is not detected by a visual inspection. This
proposed AD, however, would require repair or replacement of any
cracked MLG fitting before further flight. We have determined that
because of the safety implications and consequences associated with
cracking in the subject area, the MLG fitting must be repaired or
replaced before further flight regardless of how the crack is detected.
We note that cracking found during the ultrasonic inspection may be
repaired with oversized bushings, whereas cracking detected during the
visual inspection would require extensive repair or replacement of the
MLG fitting.
Airbus Service Bulletin A320-57-1138 specifies to contact the
manufacturer for instructions on how to repair certain conditions, but
this proposed AD would require repairing those conditions using a
method approved by the FAA or the EASA (or its delegated agent). In
light of the type of repair that would be required to address the
unsafe condition, and consistent with existing bilateral airworthiness
agreements, we have determined that, for this proposed AD, a repair
approved by the FAA or the EASA would be acceptable for compliance with
this proposed AD.
Costs of Compliance
This proposed AD would affect about 466 airplanes of U.S. registry.
The actions that are required by AD 2006-11-04 and retained in this
proposed AD take about 2 work hours per airplane, at an average labor
rate of $80 per work hour. Based on these figures, the estimated cost
of the currently required actions is $160 per airplane, per inspection
cycle.
The new proposed inspections would take between 3 and 4 work hours
per airplane, depending on the type of inspection accomplished, at an
average labor rate of $80 per work hour. Based on these figures, the
estimated cost of the new inspections specified in this proposed AD for
U.S. operators is between $111,840 and $149,120, or between $240 and
$320 per airplane, per inspection cycle.
The new proposed modification would take about 73 work hours per
airplane, at an average labor rate of $80 per work hour. Required parts
would cost $3,850 per airplane. Based on these figures, the estimated
cost of the new modification specified in this proposed AD for U.S.
operators is $4,515,540, or $9,690 per airplane.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
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 proposed 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14608 (71 FR 29578, May 23, 2006) and adding the
following new airworthiness directive (AD):
Airbus: Docket No. FAA-2008-0014; Directorate Identifier 2007-NM-
249-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by February
13, 2008.
Affected ADs
(b) This AD supersedes AD 2006-11-04.
Applicability
(c) This AD applies to Airbus Model A318, A319, A320, and A321
airplanes, certificated in any category, except airplanes on which
[[Page 2203]]
Airbus Modification 32025 has been accomplished in production.
Unsafe Condition
(d) This AD results from cracks found in the forward lug of the
main landing gear (MLG) support rib 5 fitting. We are issuing this
AD to prevent 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.
Restatement of Certain Requirements of AD 2006-11-04
Repetitive Detailed Inspections
(f) Within 8 days after June 7, 2006 (the effective date of AD
2006-11-04), 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, 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. As of the effective date of this AD, the
repetitive inspections required by paragraph (i) of this AD must be
accomplished in lieu of the repetitive inspections required by this
paragraph.
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 repetitive inspections required by paragraph (f) of this AD.
Doing the actions specified in the A318/A319/A320/A321
Nondestructive Testing Manual, Chapter 57-29-03, revision dated
February 1, 2005 (for Model A318, A319, and A320 airplanes), or
Chapter 57-29-04, revision dated May 1, 2005 (for 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: 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 (SRM), Chapter 5.C., 57-26-13, revision dated November 1,
2004; Airbus A320 SRM, Chapter 5.D., 57-26-13, revision 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.
New Requirements of This AD
New Repetitive Inspections
(i) At the applicable time specified in Table 1 of this AD, or
before further flight after a hard landing, whichever is first: Do a
visual inspection or ultrasonic inspection for cracking in the
forward lug of the support rib 5 fitting of the left and right MLG,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-57-1138, Revision 01, dated October 27, 2006. Repeat
the inspection thereafter at the applicable interval specified in
Table 1 of this AD or before further flight after a hard landing,
whichever is first, until the modification required by paragraph (k)
of this AD has been accomplished. Accomplishing the initial
inspection terminates the requirements of paragraph (f) of this AD.
Table 1.--Compliance Times
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Airplanes Initial inspection Repetitive interval
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Model A318, A319, and A320 If the most recent Within 150 flight
airplanes. inspection is a cycles after a
detailed inspection visual inspection.
done in accordance
with paragraph (f)
of this AD, inspect
within 150 flight
cycles after the
most recent
detailed inspection.
If the most recent Within 940 flight
inspection is an cycles after an
ultrasonic ultrasonic
inspection done in inspection.
accordance with
paragraph (g) of
this AD, inspect
within 940 flight
cycles after the
most recent
ultrasonic
inspection.
Model A321 airplanes........ If the most recent Within 100 flight
inspection is a cycles after a
detailed inspection visual inspection.
done in accordance
with paragraph (f)
of this AD, inspect
within 100 flight
cycles after the
most recent
detailed inspection.
If the most recent Within 630 flight
inspection is an cycles after an
ultrasonic ultrasonic
inspection done in inspection.
accordance with
paragraph (g) of
this AD, inspect
within 630 flight
cycles after the
most recent
ultrasonic
inspection.
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Corrective Action
(j) If any cracking is found during any inspection required by
paragraph (i) of this AD: Before further flight, repair or replace
the cracked MLG fitting using a method approved by either the
Manager, International Branch, ANM-116, or the EASA (or its
delegated agent).
Terminating Action
(k) Within 60 months after the effective date of this AD, modify
the rib bushings of the left and right MLG, by accomplishing all of
the applicable actions specified in the Accomplishment Instructions
of Airbus Service Bulletin A320-57-1118, Revision 03, dated April
23, 2007. Accomplishing the modification terminates the requirements
of this AD.
Credit for Actions Done According to Previous Issue of Service Bulletin
(l) For Model A319, A320, and A321 airplanes, modifying the lugs
of the support rib 5 fitting of the left and right MLG is acceptable
for compliance with the requirements of paragraph (k) of this AD if
done before the effective date of this AD in accordance with one of
the following service bulletins: Airbus Service Bulletin A320-57-
1118, dated September 5, 2002; Revision 01, dated August 28, 2003;
or Revision 02, dated August 2, 2006.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested in
[[Page 2204]]
accordance with the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in accordance with AD 2006-11-04
are approved as AMOCs for the corresponding provisions of this AD.
Related Information
(n) EASA airworthiness directive 2007-0213, dated August 7,
2007, also addresses the subject of this AD.
Issued in Renton, Washington, on December 26, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-383 Filed 1-11-08; 8:45 am]
BILLING CODE 4910-13-P