
[Federal Register Volume 76, Number 90 (Tuesday, May 10, 2011)]
[Proposed Rules]
[Pages 26962-26967]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-11335]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0389; Directorate Identifier 2007-NM-189-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2-1C, A300 B2-203, 
A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify and correct an unsafe condition on an aviation product. The 
MCAI describes the unsafe condition as:

* * * [C]racks * * * in sections 13 to 18 of the fuselage between 
rivets of longitudinal lap joints between frames 18 and 80 which 
could affect the structural integrity of the fuselage if not 
corrected.

* * * * *
The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by June 24, 2011.

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 W12-40, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; e-mail: account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
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 Operations 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; 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-2011-0389; 
Directorate Identifier 2007-NM-189-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 based on 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 December 20, 1989, we issued AD 90-01-10, Amendment 39-6448 (55 
FR 261, January 4, 1990). That AD required actions intended to address 
an unsafe condition on the products listed above.
    Since we issued AD 90-01-10, Airbus has refined the inspection 
program for cracking at areas of the fuselage defined in AD 90-01-10 as 
``special areas'' (paragraph A.1. of AD 90-01-10), ``standard areas'' 
(paragraph A.2. of AD 90-01-10), and ``modified or repaired areas'' 
(paragraph A.3. of AD 90-01-10). The new inspection program is designed 
to allow airplanes to reach their limit of validity (LOV). Certain 
compliance times are reduced and certain other compliance times are 
extended.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2007-0091, dated April 10, 2007, and corrected 
June 23, 2008 (referred to after this as ``the MCAI''), to correct an 
unsafe condition for the specified products. The MCAI states:

This Airworthiness Directive (AD) is issued in order to prevent 
cracks development in sections 13 to 18 of the fuselage between 
rivets of longitudinal lap joints between frames 18 and 80 which 
could affect the structural integrity of the fuselage if not 
corrected.
    This new AD:
    --Retains the requirements of DGAC AD 1989-061-092(B)R4 [which 
corresponds to FAA AD 90-01-10], which is cancelled;
    --Takes into account a new inspection program as detailed in 
AIRBUS Service Bulletins (SB) A300-53-0211 Revision 7, which will 
allow A300 aircraft to reach the Limit of Validity (LOV).
    This AD has been republished to correctly refer to SB A300-53-
0211 in Note 2 of the Compliance section.

The inspection program consists of repetitive detailed inspections for 
disbonding and cracking of the fuselage inner doubler; eddy current and 
ultrasonic inspections of the fuselage longitudinal lap joints for 
cracking; and repair if necessary (i.e., repairing any cracking or 
disbonding, or contacting Airbus for repair instructions and doing the 
repair). You may obtain further information by examining the MCAI in 
the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletin A300-53-229, Revision 5, dated 
April 8,

[[Page 26963]]

1997; and Mandatory Service Bulletin A300-53-0211, Revision 07, dated 
December 1, 2006. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 5 products of U.S. registry.
    We estimate that it would take about 3,735 work-hours per product 
to comply with the new basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Based on these figures, we 
estimate the cost of the proposed AD on U.S. operators to be 
$1,587,375, or $317,475 per product.

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 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 this 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 FAA amends Sec.  39.13 by removing Amendment 39-6448 (55 FR 
261, January 4, 1990) and adding the following new AD:

Airbus: Docket No. FAA-2011-0389; Directorate Identifier 2007-NM-
189-AD.

Comments Due Date

    (a) We must receive comments by June 24, 2011.

Affected ADs

    (b) This AD supersedes AD 90-01-10, Amendment 39-6448.

Applicability

    (c) This AD applies to Airbus Model A300 B2-1C, A300 B2-203, 
A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes; 
certificated in any category; serial numbers 0003 through 0156 
inclusive.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    This Airworthiness Directive (AD) is issued in order to prevent 
cracks development in sections 13 to 18 of the fuselage between 
rivets of longitudinal lap joints between frames 18 and 80 which 
could affect the structural integrity of the fuselage if not 
corrected.
    This new AD:
    --Retains the requirements of DGAC AD 1989-061-092(B)R4[which 
corresponds to FAA AD 90-10-10], which is cancelled;
    --Takes into account a new inspection program as detailed in 
AIRBUS Service Bulletins (SB) A300-53-0211 Revision 7, which will 
allow A300 aircraft to reach the Limit of Validity (LOV).
    This AD has been republished to correctly refer to SB A300-53-
0211 in Note 2 of the Compliance section.

The inspection program consists of repetitive detailed inspections 
for disbonding and cracking of the fuselage inner doubler; eddy 
current and ultrasonic inspections of the fuselage longitudinal lap 
joints for cracking; and repair if necessary (i.e., repairing any 
cracking or disbonding, or contacting Airbus for repair instructions 
and doing the repair).

Compliance

    (f) 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 Inspections of ``Special Areas'' and Repair or Modification 
if Necessary

    (g) For airplanes on which an eddy current inspection of the 
``special'' areas of the longitudinal lap joints has not been done 
as of the effective date of this AD in accordance with Airbus 
Mandatory Service Bulletin A300-53-0211: Prior to the accumulation 
of 24,000 total flight cycles, or within 2,000 flight cycles after 
the effective date of this AD, whichever occurs later; do an eddy 
current inspection for cracking of the ``special'' areas of the 
longitudinal lap joints, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A300-53-0211, 
Revision 07, dated December 1, 2006. If no cracking is found, repeat 
the inspection thereafter at the applicable intervals specified in 
Table 1 of this AD. If any crack is found during any inspection 
required by this paragraph, repair or modify before further flight, 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-53-

[[Page 26964]]

0211, Revision 07, dated December 1, 2006; and do the applicable 
inspection of the repaired or modified area in accordance with 
paragraph (k) of this AD. ``Special'' areas of the longitudinal lap 
joints are defined in Airbus Mandatory Service Bulletin A300-53-
0211, Revision 07, dated December 1, 2006.

    Table 1--Repetitive Intervals for Inspecting Special Areas of the
                         Longitudinal Lap Joints
------------------------------------------------------------------------
                                 Inspect special     Repeat at intervals
       For airplanes--               area--            not to exceed--
------------------------------------------------------------------------
All.........................  STGR5 LH and RH       3,600 flight cycles
                               (FR54 through FR58).
All.........................  STGR22 LH and RH      2,700 flight cycles
                               (FR26 through FR40).
All.........................  STGR22 RH (FR58       3,000 flight cycles
                               through FR65).
All.........................  STGR31 LH/RH (FR26    3,000 flight cycles
                               through FR39).
MSN 003.....................  STGR31 LH/RH (FR54    3,600 flight cycles
                               through FR58).
------------------------------------------------------------------------

     (h) For airplanes on which an eddy current inspection of the 
``special'' areas of the longitudinal lap joints has been done 
before the effective date of this AD in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-0211; except for airplanes on which a repair or modification 
of the ``special'' areas has been done in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-0211: Do the next inspection of the ``special'' areas of the 
longitudinal lap joints at the earlier of the times specified in 
paragraphs (h)(1) and (h)(2) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is 
found, repeat the inspection thereafter at the applicable intervals 
specified in Table 2 of this AD. If any crack is found during any 
inspection required by this paragraph, repair or modify before 
further flight, in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, 
dated December 1, 2006, and do the applicable inspection of the 
repaired or modified area in accordance with paragraph (k) of this 
AD. ``Special'' areas of the longitudinal lap joints are defined in 
Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated 
December 1, 2006.
    (1) Within 6,000 flight cycles after doing the last inspection 
of the ``special'' areas of the longitudinal lap joints, in 
accordance with Airbus Mandatory Service Bulletin A300-53-0211.
    (2) Within the applicable intervals specified in Table 2 of this 
AD, or within 60 days after the effective date of this AD, whichever 
occurs later.

    Table 2--Repetitive Intervals for Inspecting Special Areas of the
                         Longitudinal Lap Joints
------------------------------------------------------------------------
                                 Inspect special     Repeat at intervals
       For airplanes--               area--            not to exceed--
------------------------------------------------------------------------
All.........................  STGR5 LH and RH       3,600 flight cycles
                               (FR54 through FR58).
All.........................  STGR22 LH and RH      2,700 flight cycles
                               (FR26 through FR40).
All.........................  STGR22 RH (FR58       3,000 flight cycles
                               through FR65).
All.........................  STGR31 LH/RH (FR26    3,000 flight cycles
                               through FR39).
MSN 003.....................  STGR31 LH/RH (FR54    3,600 flight cycles
                               through FR58).
------------------------------------------------------------------------

Repetitive Inspections of ``Standard Areas'' and Repair or Modification 
If Necessary

    (i) For airplanes on which an eddy current inspection of the 
``standard'' areas of the longitudinal lap joints has not been done 
before the effective date of this AD in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-0211: At the applicable time specified in Tables 3 and 4 of 
this AD, do an eddy current inspection for cracking of the 
longitudinal lap joints in the ``standard'' areas, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A300-53-0211, Revision 07, dated December 1, 2006. Repeat 
the inspection thereafter at the applicable intervals specified in 
Tables 3 and 4 of this AD. If any crack is found during any 
inspection required by this paragraph, repair or modify before 
further flight, in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, 
dated December 1, 2006, and do the applicable inspection of the 
applicable area specified in Tables 3 and 4 of this AD. ``Standard'' 
areas of the longitudinal lap joints are defined in Airbus Mandatory 
Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.

Table 3--Initial Compliance Times and Repetitive Intervals for Inspecting Standard Areas of the Longitudinal Lap
                                                     Joints
----------------------------------------------------------------------------------------------------------------
                                      Before the accumulation                               Repeat at intervals
          For airplanes--                      of--              Inspect standard area--      not to exceed--
----------------------------------------------------------------------------------------------------------------
All...............................  32,000 total flight cycles  STGR5, 13, 22 LH and RH,   3,600 flight cycles
                                                                 STGR31 LH (FR18 through
                                                                 FR26).
All...............................  32,000 total flight cycles  STGR27 RH, STGR39 RH       8,000 flight cycles
                                                                 (FR18 through FR20A,
                                                                 FR25A, FR26).
All...............................  32,000 total flight cycles  STGR43 LH, STGR46 RH,      5,700 flight cycles
                                                                 STGR51 LH (FR19 through
                                                                 FR26).
All...............................  32,000 total flight cycles  STGR5 LH/RH (FR26 through  3,000 flight cycles
                                                                 FR40) STGR11 LH/RH (FR27
                                                                 through FR32) STGR13 LH/
                                                                 RH (FR 26 through FR28,
                                                                 FR31 through FR40)
                                                                 STGR27 LH/RH (FR 27
                                                                 through FR32) STGR43 LH/
                                                                 RH (FR 26 through FR39)
                                                                 STGR49 RH (FR26 through
                                                                 FR39).
All...............................  32,000 total flight cycles  STGR47 LH (FR26 through    5,700
                                                                 FR39).

[[Page 26965]]

 
All...............................  32,000 total flight cycles  STGR5, 13, 22 LH/RH (FR40  5,000
                                                                 through FR54).
All except MSN 0003...............  32,000 total flight cycles  STGR13, 44, 52 LH/RH       3,600
                                                                 (FR54 through FR58)
                                                                 STGR22 LH/RH (FR54,
                                                                 FR55) STGR31 LH/RH (FR54
                                                                 through FR58).
----------------------------------------------------------------------------------------------------------------

     (j) For airplanes on which an eddy current inspection of the 
``standard'' areas of the longitudinal lap joints has been done as 
of the effective date of this AD in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-0211; except for airplanes on which a repair or modification 
of the ``standard areas'' has been done in accordance with Airbus 
Mandatory Service Bulletin A300-53-0211: Do the next inspection of 
the ``standard'' areas of the longitudinal lap joints at the earlier 
of the times specified in paragraphs (j)(1) and (j)(2) of this AD, 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 
1, 2006. Thereafter, if no cracking is found, repeat the inspection 
at the applicable intervals specified in Tables 3 and 4 of this AD. 
If any crack is found during any inspection required by this 
paragraph, repair or modify before further flight, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A300-53-0211, Revision 07, dated December 1, 2006, and do 
the applicable inspection of the repaired or modified area in 
accordance with paragraph (k) of this AD. ``Standard'' areas of the 
longitudinal lap joints are defined in Airbus Mandatory Service 
Bulletin A300-53-0211, Revision 07, dated December 1, 2006.

   Table 4--Initial Compliance Times and Repetitive Intervals for Inspecting Additional Standard Areas of the
                                             Longitudinal Lap Joints
----------------------------------------------------------------------------------------------------------------
                                      Before the accumulation                               Repeat at intervals
          For airplanes--                      of--              Inspect standard area--      not to exceed--
----------------------------------------------------------------------------------------------------------------
Pre-Mod 1398......................  32,000 total flight cycles  STGR5, 13 LH/RH 22 LH      2,700 flight cycles
                                                                 (FR58 through FR65)
                                                                 STGR31 LH (FR58 through
                                                                 FR72) STGR31 RH (FR65
                                                                 through FR72).
All...............................  32,000 total flight cycles  STGR27 RH, STGR39 RH       8,000 flight cycles
                                                                 (FR58, FR59A, FR63A
                                                                 through FR65).
Post-Mod 1398.....................  32,000 total flight cycles  STGR5, 13 LH/RH 22 LH      3,000 flight cycles
                                                                 (FR58 through FR65)
                                                                 STGR31 LH (FR58 through
                                                                 FR72) STGR 31 RH (FR65
                                                                 through FR72).
Pre-Mod 1398......................  32,000 total flight cycles  STGR5, 13, 22 LH/RH (FR65  2,300 flight cycles
                                                                 through FR72).
Post-Mod 1398.....................  32,000 total flight cycles  STGR5, 13, 22 LH/RH (FR65  3,000 flight cycles
                                                                 through FR72).
All...............................  32,000 total flight cycles  STGR44 LH (FR58 through    3,000 flight cycles
                                                                 FR72) STGR52 LH/RH (FR58
                                                                 through FR65) STGR47 RH
                                                                 (FR58 through FR72)
                                                                 STGR57 LH (FR65 through
                                                                 FR72).
All...............................  24,000 total flight cycles  STGR22 RH (FR58 through    3,000 flight cycles
                                                                 FR65).
All...............................  32,000 total flight cycles  STGR6 LH/RH (FR72 through  3,000 flight cycles
                                                                 FR80) STGR24 LH/RH (FR76
                                                                 through FR80).
All...............................  32,000 total flight cycles  STRG17 LH/RH (FR76         5,700 flight cycles
                                                                 through FR80) STGR29 LH/
                                                                 RH (FR72 through FR76).
                                                                STGR35 LH/RH (FR72
                                                                 through FR80).
All...............................  27,000 total flight cycles  STGR51 LH/RH (FR72         5,700 flight cycles
                                                                 through FR80).
----------------------------------------------------------------------------------------------------------------

     (1) Within the applicable time in paragraph (j)(1)(i) or 
(j)(1)(ii) of this AD after doing the last inspection of the 
``standard'' areas of the longitudinal lap joints in accordance with 
Airbus Mandatory Service Bulletin A300-53-0211.
    (i) For longitudinal lap joints with bonded doublers: 6,000 
flight cycles.
    (ii) For longitudinal lap joints without bonded doublers: 8,000 
flight cycles.
    (2) Within the applicable time specified in Tables 3 or 4 of 
this AD, or within 60 days after the effective date of this AD, 
whichever occurs later.

Post-Repair or Modification Inspections and Repair or Modification if 
Necessary

    (k) For airplanes on which a repair or modification has been 
done in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-53-0211: At the applicable initial 
inspection time specified in Table 5 of this AD, do an eddy current 
inspection for cracking of the repaired or modified areas, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. 
If no cracking is found, repeat the inspection thereafter at the 
applicable intervals specified

[[Page 26966]]

in Table 5 of this AD. If any crack is found during any inspection 
required by this paragraph, repair or modify before further flight, 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 
1, 2006.

                              Table 5--Post-Repair or Modification Compliance Time
----------------------------------------------------------------------------------------------------------------
 Repair or retrofit solution/area--as
    identified in airbus mandatory        Initial inspection after     Follow-up inspections at intervals not to
    service bulletin A300-53-0211           repair or retrofit--                       exceed--
----------------------------------------------------------------------------------------------------------------
Repair 1: (Without cut out) also       Skin/doubler thickness.......  1,000 flight cycles.
 applicable to the solution with        < 1 inch: 10,000
 removed inner doubler.                 flight cycles after repair.
                                        = 1 inch   2,000 flight cycles.
                                        and < 2 inch: 30,000 flight
                                        cycles after repair.
                                        = 2 inch:  6,400 flight cycles.
                                        60,000 flight cycles after
                                        repair.
Repair 4 (With cut out)..............  Within 32,000 flight cycles    5,000 flight cycles.
                                        after repair.
Repair 4A (With cut out).............  Within 24,000 flight cycles    5,300 flight cycles.
                                        after repair.
Repair 7 (MSN 0095 at STGR52 LH in     Within 37,000 flight cycles    12,000 flight cycles.
 Section 16).                           after repair.
Repair 9 (MSN 0073 and 0095 STGR44 LH/ Within 36,000 flight cycles    5,000 flight cycles.
 RH in Sections 16 and 17).             after repair.
Repair 10 (Post-repair inspections in  Within 20,000 flight cycles    11,000 flight cycles.
 Figure 13).                            after repair.
Repair 2 (With cut out)..............  Within 24,000 flight cycles    5,300 flight cycles.
                                        after repair.
Repair 3 (Without cut out)...........  Within 24,000 flight cycles    5,300 flight cycles.
                                        after repair.
Retrofit 1 (Retrofit lap joint)......  Within 32,000 flight cycles    5,000 flight cycles.
                                        after retrofit.
Retrofit 2 Retrofit lower shell (4     Within 32,000 flight cycles    3,000 flight cycles.
 panel solution) STGR43 LH (FR26        after retrofit.
 through FR39), STGR43 RH (FR26
 through FR38), and STGR49 RH (FR26
 through FR38).
Retrofit 2 Retrofit lower shell (4     Within 32,000 flight cycles    5,700 flight cycles.
 panel solution) STGR 46 RH (FR19       after retrofit.
 through FR26), and STGR47 LH (FR26
 through FR39), and STGR51 LH (FR19
 through FR26).
Retrofit 3 Retrofit lower shell (3     Within 32,000 flight cycles    3,000 flight cycles.
 panel solution) STGR43 LH (FR26        after retrofit.
 through FR39), and STGR43 RH (FR26
 through FR38).
Retrofit 3 Retrofit lower shell (3     Within 32,000 flight cycles    5,700 flight cycles.
 panel solution) STGR46 RH (FR19        after retrofit.
 through FR26), and STGR51 LH (FR19
 through FR26), and STGR 54 LH (FR26
 through FR39).
Retrofit 3A (STGR43 LH/RH between      Within 32,000 flight cycles    5,000 flight cycles.
 FR37 and FR39 in Section 14).          after retrofit.
Retrofit 4 (Retrofit lap joint         Within 42,000 flight cycles    5,000 flight cycles.
 without cut out).                      after retrofit.
Retrofit 5 (Retrofit lap joint)......  Within 42,000 flight cycles    5,000 flight cycles.
                                        after retrofit.
Retrofit 6 (Retrofit lap joint)......  Within 34,000 flight cycles    12,000 flight cycles.
                                        after retrofit.
Retrofit 7 (Retrofit lap joint)......  Within 47,600 flight cycles    5,400 flight cycles.
                                        after retrofit.
----------------------------------------------------------------------------------------------------------------

Fuselage Inner Doubler Inspections and Repair if Necessary

    (l) For airplanes on which any inspections of the fuselage 
bonded inner doublers of the longitudinal lap joints in Sections 13 
through 18 (except Sections 16 and 17 at Stringer 31 left-hand and 
right-hand) for disbonding and cracking have not been done as of the 
effective date of this AD in accordance with Airbus Service Bulletin 
A300-53-229: Prior to the accumulation of 24,000 total flight cycles 
or within 15 years since new, whichever occurs first; or within 60 
days after the effective date of this AD; whichever occurs later, do 
a detailed inspection of the fuselage bonded inner doublers of the 
longitudinal lap joints in Sections 13 through 18 (except Sections 
16 and 17 at Stringer 31 left-hand and right-hand) for disbonding 
and cracking, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 
1997. If no disbonding and no cracking is found, repeat the 
inspection thereafter at the applicable intervals specified in Table 
6 of this AD.

    Table 6--Repetitive Intervals for Inspections for Disbonding and
                                Cracking
------------------------------------------------------------------------
                                    Inspect at intervals not to exceed--
            For area--
------------------------------------------------------------------------
Sections 13 and 14 as specified in  Within 7 years or 12,000 flight
 Airbus Service Bulletin A300-53-    cycles after doing the inspection,
 229.                                whichever occurs first.
Sections 15 through 18 as           Within 8.5 years or 12,000 flight
 specified in Airbus Service         cycles after doing the inspection,
 Bulletin A300-53-229.               whichever occurs first.
------------------------------------------------------------------------

     (1) If no cracking is found and ``minor'' disbonding, as 
defined in Airbus Service Bulletin A300-53-229, is found: Repeat the 
inspection thereafter at intervals not to exceed 1 year for areas 
below stringer 22, and at intervals not to exceed 2 years for areas 
above and including stringer 22.
    (2) If no cracking is found and ``major'' disbonding, as defined 
in Airbus Service Bulletin A300-53-229, is found: Within 1,000 
flight cycles after doing the inspection, repair, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
229, Revision 5, dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in 
accordance with Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.
    (m) For airplanes on which any inspections of the fuselage 
bonded inner doublers of the longitudinal lap joints in Sections 13 
through 18 (except Sections 16 and 17 at Stringer 31 left-hand and 
right-hand) for disbonding and cracking have been done as of the 
effective date of this AD in accordance with Airbus Service Bulletin 
A300-53-229; except for airplanes on which a repair of that area has 
been done in accordance with Airbus Service

[[Page 26967]]

Bulletin A300-53-229: At the applicable time specified in Table 6 of 
this AD, or within 60 days after the effective date of this AD, 
whichever occurs later, do a detailed inspection of the fuselage 
bonded inner doublers of the longitudinal lap joints in Sections 13 
through 18 (except Sections 16 and 17 at Stringer 31 left-hand and 
right-hand) for disbonding and cracking, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-229, 
Revision 5, dated April 8, 1997. If no disbonding and no cracking is 
found, repeat the inspection at the applicable intervals specified 
in Table 6 of this AD.
    (1) If no cracking is found and ``minor'' disbonding, as defined 
in Airbus Service Bulletin A300-53-229, is found: Repeat the 
inspection thereafter at intervals not to exceed 1 year for areas 
below stringer 22, and at intervals not to exceed 2 years for areas 
above and including stringer 22.
    (2) If no cracking is found and ``major'' disbonding, as defined 
in Airbus Service Bulletin A300-53-229, is found: Within 1,000 
flight cycles after doing the inspection, repair, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
229, Revision 5, dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in 
accordance with Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.
    (n) For airplanes on which any inspections of the fuselage 
bonded inner doublers of the longitudinal lap joints in Sections 16 
and 17 at Stringer 31 left-hand and right-hand for disbonding and 
cracking have not been done as of the effective date of this AD in 
accordance with Airbus Service Bulletin A300-53-229: Prior to the 
accumulation of 24,000 total flight cycles or within 12 years since 
new, whichever occurs first; or within 60 days after the effective 
date of this AD; whichever occurs later, do a detailed inspection of 
the fuselage bonded inner doubles of the longitudinal lap joints in 
Sections 16 and 17 at Stringer 31 left-hand and right-hand for 
disbonding and cracking, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997. If no disbonding and no cracking is found, 
repeat the inspection thereafter at intervals not to exceed 7 years 
or 12,000 flight cycles, whichever occurs first.
    (1) If no cracking is found and ``minor'' disbonding, as defined 
in Airbus Service Bulletin A300-53-229, is found: Repeat the 
inspection thereafter at intervals not to exceed 1 year for areas 
below stringer 22, and at intervals not to exceed 2 years for areas 
above and including stringer 22. Doing a repair in accordance with 
Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 
1997, terminates the repetitive inspections required by this 
paragraph for that area.
    (2) If no cracking is found and ``major'' disbonding, as defined 
in Airbus Service Bulletin A300-53-229, is found: Within 1,000 
flight cycles after doing the inspection, repair, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
229, Revision 5, dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in 
accordance with Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.
    (o) For airplanes on which any inspections of the fuselage 
bonded inner doublers of the longitudinal lap joints in Sections 16 
and 17 at Stringer 31 left-hand and right-hand for disbonding and 
cracking have been done as of the effective date of this AD in 
accordance with Airbus Service Bulletin A300-53-229; except 
airplanes on which a repair of that area has been done in accordance 
with Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 
flight cycles after doing the inspection, whichever occurs first; or 
within 60 days after the effective date of this AD; whichever occurs 
later, do a detailed inspection of the fuselage bonded inner doubles 
of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 
left-hand and right-hand for disbonding and cracking in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and 
corrosion are found, repeat the inspection thereafter at intervals 
not to exceed 7 years or 12,000 flight cycles, whichever occurs 
first.
    (1) If no cracking is found and ``minor'' disbonding, as defined 
in Airbus Service Bulletin A300-53-229, is found: Repeat the 
inspection thereafter at intervals not to exceed 1 year for areas 
below stringer 22, and at intervals not to exceed 2 years for areas 
above and including stringer 22. Doing a repair in accordance with 
Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 
1997, terminates the repetitive inspections required by this 
paragraph for that area.
    (2) If no cracking is found and ``major'' disbonding, as defined 
in Airbus Service Bulletin A300-53-229, is found: Within 1,000 
flight cycles after doing the inspection, repair, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
229, Revision 5, dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in 
accordance with Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.
    (p) Although Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997; and Airbus Mandatory Service Bulletin A300-53-
0211, Revision 07, dated December 1, 2006; specify to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service 
information as follows:
    (1) Although the MCAI or service information allows further 
flight after cracks are found during compliance with the required 
action, this AD requires that you repair the crack(s) before further 
flight.
    (2) The MCAI or service information does not include enforceable 
compliance times for certain actions; however, this AD requires that 
those actions be done at the enforceable times specified in this AD.
    (3) Although the MCAI or service information tells you to submit 
information to the manufacturer, paragraph (p) of this AD specifies 
that such submittal is not required.

Other FAA AD Provisions

    (q) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the International 
Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-2125; fax (425) 227-1149. Information may be e-mailed to: 
9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, 
notify your appropriate principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district 
office/certificate holding district office. The AMOC approval letter 
must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

Related Information

    (r) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2007-0091, dated April 10, 2007, corrected June 23, 2008; 
Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 
1997; and Airbus Mandatory Service Bulletin A300-53-0211, Revision 
07, dated December 1, 2006; for related information.

    Issued in Renton, Washington, on April 28, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-11335 Filed 5-9-11; 8:45 am]
BILLING CODE 4910-13-P


