[Federal Register Volume 72, Number 12 (Friday, January 19, 2007)]
[Proposed Rules]
[Pages 2469-2475]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-715]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-26856; Directorate Identifier 2006-NM-125-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus 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).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Airbus Model A300-600 series 
airplanes. The existing AD currently requires inspections of the lower 
door surrounding structure to detect cracks and corrosion; inspections 
to detect cracking of the holes of the corner doublers, the fail-safe 
ring, and the door frames of the door structures; and repair if 
necessary. The existing AD also provides for optional terminating 
action for certain inspections. This proposed AD would retain all 
requirements of the existing AD, mandate the previously optional 
terminating action, reduce the applicability of the existing AD, and 
add repetitive inspections behind scuff plates for certain affected 
airplanes. This proposed AD results from a determination that further 
rulemaking is necessary to improve the fatigue behavior of the cabin 
door surroundings. We are proposing this AD to prevent corrosion 
between the scuff plates at exit and cargo doors and fatigue cracks 
originating from certain fastener holes located in adjacent structure, 
which could result in reduced structural integrity of the door 
surroundings.

DATES: We must receive comments on this proposed AD by February 20, 
2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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: Tom Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

[[Page 2470]]

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-2007-26856; Directorate Identifier 2006-NM-125-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 July 24, 1998, we issued AD 98-16-05, amendment 39-10680 (63 FR 
40812, July 31, 1998), for all Airbus 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 
inspections of the lower door surrounding structure to detect cracks 
and corrosion; inspections to detect cracking of the holes of the 
corner doublers, the fail-safe ring, and the door frames of the door 
structures; and repair if necessary. That AD also provides for optional 
terminating action for certain inspections. That AD resulted from 
reports indicating that corrosion was found behind the scruff plates at 
exit and cargo doors, and fatigue cracks originated from certain 
fastener holes located in adjacent structure. We issued that AD to 
detect and correct such corrosion and fatigue cracking, which could 
result in reduced structural integrity of the door surroundings.

Other Relevant Rulemaking

    We have previously issued AD 97-11-03, amendment 39-10032 (62 FR 
28325, May 23, 1997), applicable to all Airbus Model A300 series 
airplanes. That AD requires inspections of the lower door surrounding 
structure to detect cracks and corrosion; inspections to detect 
cracking of the holes of the corner doublers, the fail-safe ring, and 
the door frames of the door structures; and repair if necessary. That 
AD also requires modification of the passenger/crew door frames, which 
terminates certain inspections.
    We also previously issued AD 98-16-06, amendment 39-10682 (63 FR 
40819, July 31, 1998), for all Airbus Model A310 series airplanes. That 
AD requires inspections of the lower door surrounding structure to 
detect cracks and corrosion; inspections to detect cracking of the 
holes of the corner doublers, the fail-safe ring, and the door frames 
of the door structures; and repair if necessary. That AD also provides 
for optional terminating action for certain inspections. We are 
considering further rulemaking to mandate the optional terminating 
action.

Actions Since Existing AD Was Issued

    Since we issued AD 98-16-05, the Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, issued French airworthiness directives 1991-132-124(B) R1, 
dated November 29, 2000 (to replace French airworthiness directive 91-
132-124(B), dated June 26, 1991, which is referred to in AD 98-16-05), 
and F-2004-103, dated July 7, 2004. The DGAC advises that further 
rulemaking is necessary to improve the fatigue behavior of the cabin 
door surroundings on certain Airbus Model A300-600 series airplanes and 
to remove certain airplanes from the applicability of the existing AD 
that are no longer subject to the existing requirements. Corrosion 
between the scuff plates at exit and cargo doors and fatigue cracks 
originating from certain fastener holes located in adjacent structure, 
if not corrected, could result in reduced structural integrity of the 
door surroundings.
    After the DGAC issued French airworthiness directive 1991-132-
124(B) R1 on November 29, 2000, we determined at that time that further 
rulemaking was not necessary, because the changes to AD 98-16-05 would 
be relieving in nature. However, since French airworthiness directive 
F-2004-103 mandates the previously optional modification, we now agree 
with the DGAC that further rulemaking is indeed necessary to improve 
the fatigue behavior of the cabin door surroundings, and this proposed 
AD follows from that determination.

Relevant Service Information

    Airbus has issued and revised the service bulletins in the 
following table:

                            Service Bulletins
------------------------------------------------------------------------
  Airbus Service Bulletin--            Describes procedures for--
------------------------------------------------------------------------
A300-53-6011, Revision 07,     Doing initial inspections for cracks and
 dated January 24, 2005         corrosion of the areas behind the scuff
 (Revision 3, dated February    plates below the passenger/crew doors
 4, 1991, of the service        and bulk cargo door, and repairing any
 bulletin was referenced in     cracked or corroded part or contacting
 AD 98-16-05 as an              Airbus. The inspection and repair are
 appropriate source of          essentially identical to those specified
 service information).          in Revision 3 of the service bulletin.
                                Revision 07 also revises the effectivity
                                by adding additional airplanes.
A300-53-6022, Revision 04,     Doing repetitive inspections for cracks
 dated January 24, 2005 (the    and corrosion of the areas behind the
 original issue, dated          scuff plates below the passenger/crew
 February 4, 1991, of the       doors and bulk cargo door, and repairing
 service bulletin was           any cracked/corroded part or contacting
 referenced in AD 98-16-05 as   Airbus. The inspection and repair are
 an appropriate source of       essentially identical to those specified
 service information).          in original issue of the service
                                bulletin. Revision 04 also revises the
                                effectivity by adding additional
                                airplanes.

[[Page 2471]]

 
A300-53-6018, Revision 03,     Doing repetitive inspections for cracks/
 dated July 26, 2006,           corrosion of the holes of the corner
 including Appendix 01          doublers, the fail-safe ring, and the
 (Revision 1, dated April 29,   door frames of the passenger/crew door
 1992, of the service           structures, and repairing any cracked/
 bulletin was referenced in     corroded part or contacting Airbus. The
 AD 98-16-05 as an              inspection and repair are essentially
 appropriate source of          identical to those specified in Revision
 service information).          1 of the service bulletin.
A300-53-6002, Revision 06,     Modifying the passenger/crew door
 dated May 17, 2004 (Revision   structures, which ends the repetitive
 3, dated February 22, 1992,    inspections of the holes of the corner
 of the service bulletin was    doublers specified in Airbus Service
 referenced in AD 98-16-05 as   Bulletin A300-53-6018, the fail-safe
 an appropriate source of       ring, and the door frames for certain
 service information).          airplanes. The modification includes
                                cold expansion of fastener holes; a ROTO
                                test; repair of any crack; repair of any
                                crack that cannot be eliminated per
                                Airbus; installation of new oversize
                                fasteners and modified brackets; and
                                installation of an additional steel
                                doubler. The modification is essentially
                                identical to that specified in Revision
                                3 of the service bulletin.
------------------------------------------------------------------------

    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information to ensure the continued airworthiness of these 
airplanes in France.

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 
section 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 AD 98-16-05, retain the 
requirements of the existing AD, mandate the previously optional 
terminating action, reduce the applicability of the existing AD, and 
add repetitive inspections behind scuff plates for certain affected 
airplanes. This proposed AD would also require accomplishing the 
actions specified in service information described previously.

Difference Between French Airworthiness Directive and This Proposed AD

    The applicability of French airworthiness directive 1991-132-124(B) 
R1 excludes Airbus Model A300-600 series airplanes on which Airbus 
Service Bulletin A300-53-6002, Revision 2, dated May 6, 1991 (or any 
other later approved revision), has been accomplished in service. 
However, we have not excluded those airplanes in the applicability of 
this proposed AD; rather, this proposed AD includes a requirement to 
accomplish the actions specified in Revision 06 of that service 
bulletin. This requirement would ensure that the actions specified in 
the service bulletin and required by this proposed AD are accomplished 
on all affected airplanes. Operators must continue to operate the 
airplane in the configuration required by this proposed AD unless an 
alternative method of compliance is approved.
    The service bulletins specify 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 
European Aviation Safety Agency (EASA) (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 EASA approve would be acceptable for compliance 
with this proposed AD.

Change to Existing AD

    This proposed AD would retain all requirements of AD 98-16-05. 
Since AD 98-16-05 was 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 requirements
        Requirement in  AD 98-16-05              in this proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  Paragraph (f).
Paragraph (b).............................  Paragraph (g).
Paragraph (c).............................  Paragraph (h).
Paragraph (d).............................  Paragraph (i).
Paragraph (e).............................  paragraph (j).
Paragraph (f).............................  Paragraph (k).
Paragraph (g).............................  Paragraph (l).
------------------------------------------------------------------------

    The DGAC revised the applicability of French airworthiness 
directives 1991-132-124(B) R1 and F-2004-103 to exclude Model A300-600 
series airplanes on which Airbus Modification 5068, 6514, 7201, and 
7298 have been incorporated in production. Therefore, the applicability 
of the proposed AD parallels the French airworthiness directives in 
that regard.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD. The average labor rate per work hour 
is $80.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                 Number of U.S.-
               Action                        Work hours                 Parts              Cost per airplane       registered           Fleet cost
                                                                                                                    airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Repetitive inspections behind scuff   37.....................  None...................  $2,960................               129  $381,840.
 plates.
Repetitive inspections of corner      Between 1 and 51.......  None...................  Between $80 and $4,080               129  Between $10,320 and
 doublers, fail-safe ring, and door                                                                                                $526,320.
 frames.

[[Page 2472]]

 
Terminating modification for          Between 8 and 67,        Between $580 and         Between $1,220 and                   129  Between $157,380 and
 repetitive inspection of corner       depending on kit         $11,273, depending on    $16,633.                                  $2,145,657.
 doublers, fail-safe ring, and door    purchased.               kit purchased.
 frames.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 39-10680 (63 FR 40812, July 31, 1998) and adding the 
following new airworthiness directive (AD):

Airbus: Docket No. FAA-2007-26856; Directorate Identifier 2006-NM-
125-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
20, 2007.

Affected ADs

    (b) This AD supersedes AD 98-16-05.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; 
Model A300 F4-605R and F4-622R airplanes; and Model A300 C4-605R 
Variant F airplanes; certificated in any category; excluding those 
airplanes on which Airbus Modification 5068, 6514, 7201, and 7298 
have been incorporated in production.

Unsafe Condition

    (d) This AD results from a determination that further rulemaking 
is necessary to improve the fatigue behavior of the cabin door 
surroundings. We are issuing this AD to prevent corrosion between 
the scuff plates at exit and cargo doors and fatigue cracks 
originating from certain fastener holes located in adjacent 
structure, which could result in reduced structural integrity of the 
door surroundings.

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.

Requirements of AD 98-16-05

Initial Inspection Behind Scuff Plates and Repair if Necessary

    (f) Perform an initial inspection of the areas behind the scuff 
plates below the passenger/crew doors and bulk cargo door to detect 
cracks and corrosion, in accordance with Airbus Service Bulletin 
A300-53-6011, Revision 3, dated February 4, 1991, at the time 
specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD. If any 
crack or corrosion is found during this inspection, prior to further 
flight, repair in accordance with the service bulletin. 
Accomplishment of this inspection is not required for the mid and 
aft passenger/crew doors if a steel doubler that covers the entire 
inspection area is installed.
    (1) For airplanes on which Modification 5382S6526 (for forward 
doors) and Modification 5382D4741 (for all other doors) have been 
accomplished prior to delivery of the airplane: Perform the initial 
inspection within 9 years since date of manufacture, or within 1 
year after September 4, 1998 (the effective date of AD 98-16-05), 
whichever occurs later.
    (2) For airplanes on which Modification 5382S6526 (for forward 
doors) and Modification 5382D4741 (for all other doors) have not 
been accomplished; and on which the procedures described in Airbus 
Service Information Letter (SIL) A300-53-033, Revision 2 (for all 
doors), dated November 23, 1984, have been accomplished: Perform the 
initial inspection within 5 years after accomplishment of the 
procedures described in the SIL, or within 1 year after September 4, 
1998, whichever occurs later.
    (3) For airplanes on which Modification 5382S6526 (for forward 
doors), and Modification 5382D4741 (for all other doors), and the 
procedures described in Airbus SIL A300-53-033, Revision 2, dated 
November 23, 1984, have not been accomplished: Perform the initial 
inspection within 4 years since date of manufacture, or within 1 
year after September 4, 1998, whichever occurs later.

Repetitive Inspections Behind Scuff Plates

    (g) Perform repetitive inspections of the areas behind the scuff 
plates below the passenger/crew doors and bulk cargo door to detect 
cracks and corrosion, in accordance with Airbus Service Bulletin 
A300-53-6022, dated February 4, 1991, at the applicable times 
specified in paragraphs (g)(1) and (g)(2) of this AD. Accomplishment 
of these inspections is not required for the mid and aft passenger/
crew doors if a steel doubler that covers the entire inspection area 
is installed.

[[Page 2473]]

    (1) For the forward and mid passenger/crew doors, the bulk cargo 
door, and the aft passenger/crew doors, except the upper and lower 
edges of the fail-safe ring and the upper edges of the corner 
doubler: Perform the first inspection within 5 years after 
accomplishing the inspection required by paragraph (f) of this AD; 
and repeat the inspection thereafter at intervals not to exceed 5 
years.
    (2) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew doors: 
Perform the first inspection within 5 years or 6,000 landings after 
accomplishing the inspection required by paragraph (f) of this AD, 
whichever occurs first; and repeat the inspection thereafter at 
intervals not to exceed 5 years or 6,000 landings, whichever occurs 
first.

Repair of Scuff Plates if Necessary

    (h) If any crack is found during any inspection required by 
paragraph (g) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A300-53-6022, dated February 
4, 1991. Thereafter, perform the repetitive inspections required by 
paragraph (g) of this AD at the applicable times specified in 
paragraphs (g)(1) and (g)(2) of this AD.
    (i) If corrosion is found during any inspection required by 
paragraph (g) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A300-53-6022, dated February 
4, 1991. Thereafter, perform the repetitive inspections required by 
paragraph (g) of this AD at the applicable times specified in 
paragraph (i)(1) or (i)(2) of this AD.
    (1) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew doors, 
and for the mid passenger/crew door: Inspect at intervals not to 
exceed 5 years or 5,000 landings, whichever occurs first.
    (2) For the forward passenger/crew doors and bulk cargo doors: 
Inspect at intervals not to exceed 5 years.

Initial Inspection of Corner Doublers, Fail-Safe Ring, and Door 
Frames

    (j) Perform an inspection to detect cracking of the holes of the 
corner doublers, the fail-safe ring, and the door frames of the 
left- and right-hand forward, mid, and aft passenger/crew door 
structures, in accordance with Airbus Service Bulletin A300-53-6018, 
Revision 1, dated April 29, 1992, and at the applicable time 
specified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD.
    (1) For the upper corners of the forward doors: Inspect prior to 
the accumulation of 20,000 total landings, or within 2,000 landings 
after September 4, 1998, whichever occurs later.
    (2) For the lower corners of the forward doors: Inspect prior to 
the accumulation of 20,000 total landings, or within 4,000 landings 
after September 4, 1998, whichever occurs later.
    (3) For the upper and lower corners of the mid doors: Inspect 
prior to the accumulation of 20,000 total landings, or within 2,000 
landings after September 4, 1998, whichever occurs later.
    (4) For the upper and lower corners of the aft doors, and for 
the parts underneath the corners of the upper door frames: Inspect 
prior to the accumulation of 20,000 total landings, or within 4,000 
landings after September 4, 1998, whichever occurs later.

Repetitive Inspections of Corner Doublers, Fail-Safe Ring, and Door 
Frames

    (k) Repeat the inspections required by paragraph (j) of this AD 
at the applicable times specified in paragraphs (k)(1), (k)(2), 
(k)(3), (k)(4), and (k)(5) of this AD.
    (1) For the upper corners of the forward doors: Inspect at 
intervals not to exceed 6,000 landings.
    (2) For the lower corners of the forward doors: Inspect at 
intervals not to exceed 10,000 landings.
    (3) For the upper and lower corners of the mid and aft doors on 
which an inspection required by paragraph (j) of this AD was 
accomplished using a ROTO test technique: Inspect at intervals not 
to exceed 8,000 landings.
    (4) For the upper and lower corners of the mid and aft doors on 
which an inspection required by paragraph (j) of this AD was 
accomplished using an X-ray technique: Inspect at intervals not to 
exceed 3,500 landings.
    (5) For the areas around the fasteners in the vicinity of 
stringer 12 on the upper door frames of the aft doors on which an 
inspection required by paragraph (j) of this AD was accomplished 
using a visual technique: Inspect at intervals not to exceed 6,900 
landings.

Repair of Corner Doublers, Fail-Safe Ring, and/or Door Frames If 
Necessary

    (l) If any crack is found during any inspection required by 
paragraph (j) or (k) of this AD: Prior to further flight, accomplish 
the requirement of paragraph (l)(1) or (l)(2) of this AD, as 
applicable.
    (1) If any crack is found, and the crack can be eliminated using 
the method specified in Airbus Service Bulletin A300-53-6018, 
Revision 1, dated April 29, 1992; or Revision 02, excluding Appendix 
01, dated November 27, 2000: Prior to further flight, repair the 
crack in accordance with that service bulletin.
    (2) If any crack is found, and the crack cannot be eliminated 
using the method specified in Airbus Service Bulletin A300-53-6018, 
Revision 1, dated April 29, 1992; or Revision 02, dated November 27, 
2000: Prior to further flight, repair the crack in accordance with a 
method approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate.

New Requirements of This AD

New Revision of Service Bulletins

    (m) As of the effective date of this AD, use only the applicable 
service bulletins specified in Table 1 of this AD; except where the 
service bulletins recommend contacting Airbus for appropriate 
action, before further flight, repair the cracked part using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the European Aviation Safety 
Agency (EASA) (or its delegated agent).

               Table 1.--New Revision of Service Bulletins
------------------------------------------------------------------------
                                              In accordance with the
     Do the action(s) required by--       Accomplishment Instructions of
                                            Airbus Service Bulletin--
------------------------------------------------------------------------
(1) Paragraph (f) of this AD...........  A300-53-6011, Revision 07,
                                          dated January 24, 2005.
(2) Paragraphs (g) through (i) of this   A300-53-6022, Revision 04,
 AD.                                      dated January 24, 2005.
(3) Paragraphs (j), (k), and (l)(1) of   A300-53-6018, Revision 03,
 this AD.                                 excluding Appendix 01, dated
                                          July 26, 2006.
------------------------------------------------------------------------

Initial Inspection Behind Scuff Plates and Repair If Necessary for 
Additional Airplanes

    (n) Perform an initial inspection of the areas behind the scuff 
plates below the passenger/crew doors and bulk cargo door to detect 
cracks and corrosion, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-6011, Revision 07, 
dated January 24, 2005; at the applicable time specified in Table 2 
of this AD. If any crack or corrosion is found during this 
inspection, before further flight, repair in accordance with the 
service bulletin. Accomplishment of this inspection is not required 
for the mid and aft passenger/crew doors if a steel doubler that 
covers the entire inspection area is installed.

[[Page 2474]]



            Table 2.--Compliance Time Initial Inspection Behind Scuff Plate for Additional Airplanes
----------------------------------------------------------------------------------------------------------------
                                                                    Compliance time  (whichever occurs later)
       For airplanes on which--             And on which--     -------------------------------------------------
                                                                       Threshold               Grace period
----------------------------------------------------------------------------------------------------------------
(1) Modification 5382S6526 (for        None...................  Within 108 months after  Within 12 months after
 forward doors) and Modification                                 first flight.            the effective date of
 5382D4485 (for all other doors) have                                                     this AD.
 been done before the date of
 issuance of the original French
 standard airworthiness certificate
 or the date of issuance of the
 original French export certificate
 of airworthiness.
(2) Modification 5382S6180 (for        None...................  Within 108 months after  Within 12 months after
 forward doors) and Modification                                 first flight.            the effective date of
 5382D4741 or 5382D4485 (for all                                                          this AD.
 other doors) have been done before
 the date of issuance of the original
 French standard airworthiness
 certificate or the date of issuance
 of the original French export
 certificate of airworthiness.
(3) Modification 5382S6526 (for        The actions specified    Within 60 months after   Within 12 months after
 forward doors) and Modification        in Airbus Service        accomplishing the        the effective date of
 5382D4485 (for all other doors) have   Information Letter       actions specified in     this AD.
 not been done before the effective     (SIL) A300-53-033,       the SIL.
 date of this AD.                       Revision 2 (for all
                                        doors), dated November
                                        23, 1984, have been
                                        done.
(4) Modification 5382S6180 (for        The actions specified    Within 60 months after   Within 12 months after
 forward doors) and Modification        in Airbus SIL A300-53-   accomplishing the        the effective date of
 5382D4741 or 5382D4485 (for all        033, Revision 2 (for     actions specified in     this AD.
 other doors) have not been done        all doors), dated        the SIL.
 before the effective dated of this     November 23, 1984,
 AD.                                    have been done.
(5) Modification 5382S6526 (for        The actions specified    Within 48 months since   Within 12 months after
 forward doors) and Modification        in Airbus SIL A300-53-   the date of issuance     the effective date of
 5382D4485 (for all other doors) have   033, Revision 2, dated   of the original French   this AD.
 not been done before the effective     November 23, 1984,       standard airworthiness
 date of this AD.                       have not been done.      certificate or the
                                                                 date of issuance of
                                                                 the original French
                                                                 export certificate of
                                                                 airworthiness.
(6) Modification 5382S6180 (for        The actions specified    Within 48 months since   Within 12 months after
 forward doors) and Modification        in Airbus SIL A300-53-   the date of issuance     the effective date of
 5382D4741 or 5382D4485 (for all        033, Revision 2, dated   of the original French   this AD.
 other doors) have not been done        November 23, 1984,       standard airworthiness
 before the effective date of this AD.  have not been done.      certificate or the
                                                                 date of issuance of
                                                                 the original French
                                                                 export certificate of
                                                                 airworthiness.
----------------------------------------------------------------------------------------------------------------

Repetitive Inspections behind Scuff Plates for Additional Airplanes

    (o) For airplanes identified in Table 2 of this AD: Perform 
repetitive inspections of the areas behind the scuff plates below 
the passenger/crew doors and bulk cargo door to detect cracks and 
corrosion, in accordance with Airbus Service Bulletin A300-53-6022, 
Revision 04, dated January 24, 2005, at the applicable times 
specified in paragraphs (o)(1) and (o)(2) of this AD. Accomplishment 
of these inspections is not required for the mid and aft passenger/
crew doors if a steel doubler that covers the entire inspection area 
is installed.
    (1) For the forward and mid passenger/crew doors, the bulk cargo 
door, and the aft passenger/crew doors, except the upper and lower 
edges of the fail-safe ring and the upper edges of the corner 
doubler: Perform the first inspection within 60 months after 
accomplishing the inspection required by paragraph (n) of this AD; 
and repeat the inspection thereafter at intervals not to exceed 60 
months.
    (2) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew doors: 
Perform the first inspection within 60 months or 6,000 landings 
after accomplishing the inspection required by paragraph (n) of this 
AD, whichever occurs first; and repeat the inspection thereafter at 
intervals not to exceed 60 months or 6,000 landings, whichever 
occurs first.

Repair of Scuff Plates If Necessary

    (p) If any crack is found during any inspection required by 
paragraph (o) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A300-53-6022, Revision 04, 
dated January 24, 2005. Thereafter, perform the repetitive 
inspections required by paragraph (o) of this AD at the applicable 
times specified in paragraphs (o)(1) and (o)(2) of this AD.
    (q) If corrosion is found during any inspection required by 
paragraph (o) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A300-53-6022, Revision 04, 
dated January 24, 2005. Thereafter, perform the repetitive 
inspections required by paragraph (g) of this AD at the applicable 
times specified in paragraph (q)(1) or (q)(2) of this AD.
    (1) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew doors, 
and for the mid passenger/crew door: Inspect at intervals not to 
exceed 60 months or 5,000 landings, whichever occurs first.
    (2) For the forward passenger/crew doors and bulk cargo doors: 
Inspect at intervals not to exceed 60 months.

Terminating Modification for Repetitive Inspection of Corner 
Doublers, Fail-Safe Ring, and Door Frames

    (r) Before the accumulation of 30,000 total flight cycles since 
the date of issuance of the original French standard airworthiness 
certificate or the date of issuance of the original French export 
certificate of airworthiness, or during the next inspection required 
by paragraph (k) of this AD, whichever occurs later: Modify the 
passenger/crew door structures in accordance

[[Page 2475]]

with the Accomplishment Instructions of Airbus Service Bulletin 
A300-53-6002, Revision 06, dated May 17, 2004. Accomplishment of 
this modification constitutes terminating action for the inspections 
required by paragraphs (j) and (k) of this AD. The inspections 
required by paragraphs (f) and (n) of this AD, as applicable, must 
be done before accomplishing this modification.

Earlier Revisions of Service Bulletins

    (s) Actions done before the effective date of this AD in 
accordance with the service bulletins identified in Table 3 of this 
AD, are acceptable for compliance with the corresponding 
requirements of this AD.

            Table 3.--Earlier Revisions of Service Bulletins
------------------------------------------------------------------------
                                  Revision
    Airbus Service Bulletin        level                 Date
------------------------------------------------------------------------
(1) A300-53-6002..............           03  February 22, 1992.
(2) A300-53-6002..............            4  July 13, 1992.
(3) A300-53-6002..............           05  September 7, 2000.
(4) A300-53-6011..............           04  July 2, 1996.
(5) A300-53-6011..............           05  September 7, 2000.
(6) A300-53-6011..............           06  November 12, 2002.
(7) A300-53-6018, excluding              02  November 27, 2000.
 Appendix 01.
(8) A300-53-6022..............           01  July 2, 1996.
(9) A300-53-6022..............           02  September 7, 2000.
(10) A300-53-6022.............           03  November 12, 2002.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (t)(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) AMOCs approved previously in accordance with AD 98-16-05 are 
approved as AMOCs for the corresponding provisions of paragraphs (f) 
through (l) of this AD.
    (3) 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

    (u) French airworthiness directives 1991-132-124(B) R1, dated 
November 29, 2000, and F-2004-103, dated July 7, 2004, also address 
the subject of this AD.

    Issued in Renton, Washington, on January 8, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-715 Filed 1-18-07; 8:45 am]
BILLING CODE 4910-13-P