[Federal Register: January 26, 2006 (Volume 71, Number 17)]
[Proposed Rules]
[Page 4313-4317]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26ja06-17]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 4313]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23690; Directorate Identifier 2004-NM-133-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and B4 Series
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)
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede two existing airworthiness
directives (AD) that apply to certain Airbus Model A300 B2, A300 B4,
and A300-600 series airplanes. One AD currently requires an inspection
for cracks of the lower outboard flange of gantry No. 4 in the main
landing gear (MLG) bay area, and repair if necessary. The other AD
currently requires, among other actions, repetitive inspections of the
gantry lower flanges, and repair if necessary. The proposed AD also
would require new repetitive inspections for cracks in the lower flange
of certain gantries, and repair if necessary, which would end the
existing inspection requirements. The proposed AD also would provide
for optional terminating actions for the new repetitive inspections.
This proposed AD results from a report of a large fatigue crack along
the outboard flange of beam No. 4 and a subsequent determination that
existing inspections are inadequate. We are proposing this AD to detect
and correct fatigue cracks in the lower flanges of gantries 1 through 5
inclusive in the MLG bay area, which could result in reduced structural
integrity of the fuselage, and consequent rapid decompression of the
airplane.
DATES: We must receive comments on this proposed AD by February 27,
2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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 proposed AD.
FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2006-23690; Directorate Identifier 2004-NM-133-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
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 proposed 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.
Discussion
On December 23, 2003, we issued AD 2003-26-10, amendment 39-13408
(69 FR 867, January 7, 2004), for certain Airbus Model A300 B2 and B4
series 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). That AD requires a one-time inspection for
cracking of the lower outboard flange of gantry No. 4 in the main
landing gear (MLG) bay area, and repair if necessary. That AD resulted
from a report of cracks found on the lower outboard flange of gantry
No. 4 in the MLG bay area. We issued that AD to find and fix cracking
of the lower outboard flange of gantry No. 4, which could result in
reduced structural integrity of the fuselage, and consequent rapid
decompression of the airplane.
On August 31, 2004, we issued AD 2004-18-13, amendment 39-13792 (69
FR 55329, September 14, 2004), for certain Airbus Model A300 B2 and B4
series airplanes, and Model A300 B4-601, B4-603, B4-605R, B4-620, B4-
622R, C4-605R Variant F, and F4-605R airplanes. For certain airplanes,
that AD requires a one-time inspection for cracking of the gantry lower
flanges, and repair if necessary. That AD also requires repetitive
inspections of the gantry lower flanges; repair if necessary; and
reinforcement of the left-hand and right-hand gantry. That AD resulted
from the issuance of mandatory
[[Page 4314]]
continuing airworthiness information by a foreign civil airworthiness
authority. We issued that AD to detect and correct cracking of the
gantry lower flanges in the MLG bay area, which could result in
decompression of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2004-18-13, we have received a report that,
during an inspection required by that AD, a large fatigue crack running
along the outboard flange of beam No. 4 was found. The report also
indicates that the inspection requirements of ADs 2004-18-13 and 2003-
26-10 do not adequately detect cracks in the lower flange of the left
and right gantries 1 through 5 inclusive in the MLG bay area. Such
cracks, if not detected and corrected, could result in reduced
structural integrity of the fuselage, and consequent rapid
decompression of the airplane.
Relevant Service Information
Airbus has issued Revision 01 of Service Bulletins A300-53-0379
(for Model A300 B2 and B4 series airplanes) and A300-53-6152 (for Model
A300-600 series airplanes), both dated October 4, 2005. The service
bulletins describe procedures for doing repetitive ultrasonic
inspections or high frequency eddy current inspections, including
rework of the pressure diaphragm, for cracks in the lower flange of the
left and right gantries 1 through 5 inclusive between FR47 and FR54;
and repairing any crack. The threshold for the compliance time ranges
between 1,950 and 54,000 total flight cycles depending on the airplane
configuration; the grace period is 1,500 flight cycles.
Accomplishing the actions specified in the service information
described previously is intended to adequately address the unsafe
condition. The DGAC mandated that service information and issued French
airworthiness directive F-2005-091 R1, September 28, 2005, to ensure
the continued airworthiness of these airplanes in France. The DGAC also
approved the following service information as optional terminating
actions for the repetitive ultrasonic and high frequency eddy current
inspections described previously:
Airbus Service Bulletins A300-53-0380, dated August 5,
2005 (for Model A300 B2 and B4 series airplanes), and A300-53-6153,
dated August 24, 2005 (for Model A300-600 series airplanes). The
service bulletins describe procedures for reinforcing the flanges of
the left and right portals 1 through 5 inclusive between FR47 and FR54
of the landing gear, including a rotating probe inspection for cracks
of the holes and repair if necessary.
Airbus Service Bulletins A300-53-0360, dated May 3, 2002
(for Model A300 B2 and B4 series airplanes), and A300-53-6132, dated
February 5, 2002 (for Model A300-600 series airplanes). The service
bulletins describe procedures for reinforcing portals 3, 4, and 5 of
the plates/skin.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
Sec. 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 AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede ADs 2003-26-10 and 2004-18-13 and
retain certain requirements of AD 2003-26-10 and all requirements of AD
2004-18-13. This proposed AD also would require accomplishing the
actions specified in Airbus Service Bulletins A300-53-0379 and A300-53-
6152 described previously and would provide for optional terminating
actions specified in the remaining service information described
previously, except as discussed under ``Difference Between the Proposed
AD and Service Information.''
Difference Between the Proposed AD and Service Information
The service information 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 that we or the
DGAC (or its delegated agent) approve. 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 we or the DGAC approve would be
acceptable for compliance with this proposed AD.
Change to Existing AD
Since ADs 2003-26-10 and 2004-18-13 were issued, the AD format has
been revised, and certain paragraphs have been rearranged. As a result,
the corresponding paragraph identifiers have changed in this proposed
AD, as listed in the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2003-26-10 this proposed AD
------------------------------------------------------------------------
Paragraph (a)............................. Paragraph (f).
Paragraph (b)............................. Paragraph (g).
-------------------------------------------
Requirement in AD 2004-18-13 Corresponding requirement in
this proposed AD
-------------------------------------------
Paragraph (a)............................. Paragraph (h).
Paragraph (b)............................. Paragraph (i).
Paragraph (c)............................. Paragraph (j).
------------------------------------------------------------------------
Costs of Compliance
This proposed AD would affect about 165 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this proposed AD. Not all actions must be completed on all
airplanes.
Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per airplane registered Fleet cost
rate per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
One-time inspection (required by 1 $65 None.................. $65.................. 23 $1,495.
AD 2003-26-10).
One-time inspection (required by 4 65 None.................. 260.................. 43 11,180.
AD 2004-18-13).
[[Page 4315]]
Repetitive inspections (required 12 65 None.................. 780, per inspection 78 60,840, per
by AD 2004-18-13). cycle. inspection cycle.
Repetitive inspections (new 16 65 None.................. 1,040, per inspection 78 81,120, per
proposed actions). cycle. inspection cycle.
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Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Optional action Work hours Average labor Parts Cost per registered
rate per hour airplane airplanes
----------------------------------------------------------------------------------------------------------------
Reinforcement specified in 807............ $65 Between $87,100 Between 23
Airbus Service Bulletin A300- and $121,560 $139,555 and
53-0380, dated August 5, depending on $174,015
2005. kit purchased. depending on
airplane
configuration.
Reinforcement specified in 807............ 65 Between $82,460 Between 120
Airbus Service Bulletin A300- and $87,070 $134,915 and
53-6153, dated August 24, depending on $139,525
2005. kit purchased. depending on
airplane
configuration.
Reinforcement specified in Between 24 and 65 Between $250 Between $1,810 23
Airbus Service Bulletin A300- 128 depending and $1,000 and $9,320
53-0360, dated May 3, 2002. on airplane depending on depending on
configuration. kit purchased. airplane
configuration.
Reinforcement specified in 109............ 65 Between $260 Between $7,345 120
Airbus Service Bulletin A300- and $950 and $8,035
53-6132, dated February 5, depending on depending on
2002. kit purchased. airplane
configuration.
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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 amendments 39-13408 (69 FR 867, January 7, 2004) and 39-13792
(69 FR 55329, September 14, 2004) and adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA-2006-23690; Directorate Identifier 2004-NM-
133-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by February
27, 2006.
Affected ADs
(b) This AD supersedes ADs 2003-26-10 and 2004-18-13.
Applicability
(c) This AD applies to Airbus airplanes identified in Table 1 of
this AD, certificated in any category.
[[Page 4316]]
Table 1.--Applicability
------------------------------------------------------------------------
Except for those airplanes on
Affected Airbus airplanes which--
------------------------------------------------------------------------
(1) All Model A300 B2-1A, B2-1C, B2K- None.
3C, and B2-203 airplanes.
(2) All Model A300 B4-2C, B4-103, and None.
B4-203 airplanes.
(3) Model A300 B4-601, B4-603, B4-620, Airbus Modification 12169 has
and B4-622 airplanes. been incorporated in
production.
(4) Model A300 B4-605R and B4-622R Airbus Modification 12169 has
airplanes. been incorporated in
production.
(5) Model A300 F4-605R and F4-622R Airbus Modification 12169 has
airplanes. been incorporated in
production.
(6) Model A300 C4-605R Variant F Airbus Modification 12169 has
airplanes. been incorporated in
production.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from a report of a large fatigue crack along
the outboard flange of beam No. 4. We are issuing this AD to detect
and correct fatigue cracks in the lower flanges of the left and
right gantries 1 through 5 inclusive in the main landing gear (MLG)
bay area, which could result in reduced structural integrity of the
fuselage, and consequent rapid decompression 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.
Restatement of Requirements of AD 2003-26-10
One-Time Inspection
(f) For airplanes on which Airbus Modification 10147 has not
been done: At the later of the times specified in paragraphs (f)(1)
and (f)(2) of this AD: Do a one-time detailed inspection for
cracking of the lower outboard flange of gantry No. 4 in the main
landing gear bay area per paragraph 4.2.1 of Airbus All Operators
Telex (AOT) A300-53A0371, Revision 01 (for Model A300 B2 and B4
series airplanes); or AOT A300-53A6145, Revision 01 (for Model A300-
600 series airplanes); both dated September 10, 2003; as applicable.
(1) Before the accumulation of 8,000 total flight cycles since
the date of issuance of the original Airworthiness Certificate or
the date of issuance of the Export Certificate of Airworthiness,
whichever is first.
(2) Within 30 days after January 22, 2004 (the effective date AD
2003-26-10).
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
Repair
(g) Repair any cracking found during the inspection required by
paragraph (f) of this AD before further flight, per a method
approved by either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the Direction Generale de
l'Aviation Civile (or its delegated agent).
Restatement of Requirements of AD 2004-18-13
One-time Inspection and Corrective Action
(h) For Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes,
and Model A300 B4-2C, B4-103, and B4-203 airplanes, on which Airbus
Modification 3474 has been done: Prior to the accumulation of 16,300
total flight cycles, or within 500 flight cycles after July 30, 1998
(the effective date of AD 98-13-37), whichever occurs later, perform
a one-time ultrasonic inspection for cracking of the gantry lower
flanges in the MLG bay area, in accordance with Airbus AOT 53-11,
dated October 13, 1997.
(1) If any cracking is detected, prior to further flight, repair
in accordance with the AOT.
(2) If no cracking is detected, no further action is required by
this paragraph.
Repetitive Inspections and Corrective Actions
(i) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622R, C4-
605R Variant F airplanes, and F4-605R airplanes, on which Airbus
Modification 12169 has not been done in production: Perform the
requirements of paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of
this AD, in accordance with Airbus Service Bulletin A300-53-6128,
dated March 5, 2001.
(1) At the later of the times specified in paragraphs (i)(1)(i)
and (i)(1)(ii) of this AD, perform initial ultrasonic inspections or
high-frequency eddy current inspections for cracks of the lower
flanges of gantries 3, 4, and 5 between fuselage frames FR47 and
FR54, in accordance with the Accomplishment Instructions, including
the Synoptic Chart contained in Figure 2, sheets 1 through 5
inclusive, of the service bulletin.
(i) In accordance with the thresholds specified in the Synoptic
Chart contained in Figure 2, sheets 1 through 5 inclusive, of the
service bulletin; or
(ii) Within 200 flight cycles after October 19, 2004 (the
effective date AD 2004-18-13).
(2) Perform repetitive ultrasonic inspections or high-frequency
eddy current inspections for cracks of the lower flanges of gantries
3, 4, and 5 between fuselage frames FR47 and FR54, in accordance
with the thresholds and Accomplishment Instructions, including the
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive,
of the service bulletin.
(3) Perform repairs and reinforcements, in accordance with the
thresholds and the Accomplishment Instructions, including the
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive,
of the service bulletin, except as specified in paragraph (i)(4) of
this AD.
(4) If a new crack is found during any action required by
paragraph (i)(1), (i)(2) or (i)(3) of this AD and the Synoptic Chart
contained in Figure 2, sheets 1 through 5 inclusive, of the service
bulletin specifies to contact Airbus for appropriate action: Prior
to further flight, repair per a method approved by the Manager,
International Branch, ANM-116, or the Direction Generale de
l'Aviation Civile (DGAC) (or its delegated agent).
Credit for Inspections Accomplished in Accordance With AOT
(j) Any inspection accomplished before October 19, 2004, in
accordance with Airbus AOT 53-11, dated October 13, 1997, is
acceptable for compliance with the corresponding inspection
specified in paragraph (i)(1) of this AD, for that inspection area
only. Operators must do the applicable inspections in paragraph
(i)(1) of this AD for the remaining inspection areas.
New Requirements of This AD
Repetitive Inspections
(k) At the later of the applicable times specified in the
``Threshold (FC)'' and ``Grace Period'' columns of Tables 1 and 2 in
paragraph 1.E of the applicable service bulletin in Table 2 of this
AD: Do an ultrasonic inspection or high frequency eddy current
(HFEC) inspection, including rework of the pressure diaphragm, for
cracks in the lower flanges of the left and right gantries 1 through
5 inclusive between FR47 and FR54, in accordance with the
Accomplishment Instructions of the applicable service bulletin in
Table 2 of this AD. Repeat the inspection at the applicable times
specified in the ``Interval (FC)'' column of Tables 1 and 2 in
paragraph 1.E of the applicable service bulletin in Table 2 of this
AD. Accomplishment of the initial inspection ends the inspections
required by paragraphs (f), (h), and (i) of this AD.
[[Page 4317]]
Table 2.--Service Bulletins
------------------------------------------------------------------------
Airbus service bulletin-- For airplanes identified in--
------------------------------------------------------------------------
(1) A300-53-0379, Revision 01, dated Paragraphs (c)(1) and (c)(2) of
October 4, 2005. this AD inclusive.
(2) A300-53-6152, Revision 01, dated Paragraphs (c)(3) through
October 4, 2005. (c)(6) of this AD inclusive.
------------------------------------------------------------------------
Corrective Action
(l) If any crack is detected during any ultrasonic or HFEC
inspection required by paragraph (k) of this AD, before further
flight, repair the crack in accordance with the Accomplishment
Instructions of the applicable service bulletin in Table 2 of this
AD, except as provided by paragraph (n) of this AD.
Optional Terminating Actions
(m) Accomplishment of the actions specified in Table 3 of this
AD ends the repetitive inspections required by paragraph (k) of this
AD.
Table 3.--Optional Terminating Actions
----------------------------------------------------------------------------------------------------------------
By doing all the
actions in accordance For airplanes
Before or at the same time with-- Reinforce-- with the accomplishment identified in--
instructions of--
----------------------------------------------------------------------------------------------------------------
(1) The actions required by paragraph The flanges of the left Airbus Service Bulletin Paragraphs (c)(1) and
(k) of this AD and the action and right portals 1 A300-53-0380, dated (c)(2) of this AD
specified in paragraph (m)(2) of through 5 inclusive August 5, 2005, except inclusive.
this AD. between FR47 and FR54 as provided by
of the landing gear, paragraph (n) of this
including a rotating AD.
probe inspection for
cracks of holes and
repair if necessary.
Airbus Service Bulletin Paragraphs (c)(3)
A300-53-6153, dated through (c)(6) of this
August 24, 2005, AD inclusive.
except as provided by
paragraph (n) of this
AD.
(2) The actions required by paragraph Portals 3, 4, and 5 of Airbus Service Bulletin Paragraphs (c)(1) and
(k) of this AD. the plates/skin. A300-53-0360, dated (c)(2) of this AD
May 3, 2002, except as inclusive.
provided by paragraph
(n) of this AD.
Airbus Service Bulletin Paragraphs (c)(3)
A300-53-6132, dated through (c)(6) of this
February 5, 2002, AD inclusive.
except as provided by
paragraph (n) of this
AD.
----------------------------------------------------------------------------------------------------------------
Repair of Certain Cracks
(n) Where the applicable service bulletin recommends contacting
Airbus for appropriate action: Before further flight, repair the
crack in accordance with a method approved by the Manager,
International Branch, ANM-116; or the DGAC (or its delegated agent).
Credit for Original Service Bulletins
(o) Accomplishing the inspections and repair before the
effective date of this AD in accordance with Airbus Service Bulletin
A300-53-0379, dated May 9, 2005; or Airbus Service Bulletin A300-53-
6152, dated May 9, 2005; as applicable; is acceptable for compliance
with the corresponding requirements of paragraphs (k) and (l) of
this AD.
No Inspection Report
(p) Although the service bulletins in this AD specify to submit
certain information to the manufacturer, this AD does not include
that requirement.
Alternative Methods of Compliance (AMOCs)
(q)(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
(r) French airworthiness directive F-2005-091 R1, issued
September 28, 2005, also addresses the subject of this AD.
Issued in Renton, Washington, on January 19, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-972 Filed 1-25-06; 8:45 am]
BILLING CODE 4910-13-P