AD 2007-04-11

[Federal Register Volume 72, Number 38 (Tuesday, February 27, 2007)]
[Rules and Regulations]
[Pages 8604-8608]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: E7-2512]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25890; Directorate Identifier 2006-NM-115-AD; 
Amendment 39-14943; AD 2007-04-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Airbus Model A300 B2, B4-100, and B4-200 
series airplanes. That AD currently requires supplemental structural 
inspections to detect fatigue cracking, and repair of cracked 
structure. This new AD requires revising the maintenance program by 
incorporating new and revised supplemental structural inspections, 
inspection intervals, and repairs; and repair of any damaged, cracked, 
or corroded structure; which would end the existing supplement 
structural inspections. This AD results from a review of service 
history and reports received from the current supplemental structural 
inspection document program. We are issuing this AD to prevent reduced 
structural integrity of these airplanes due to fatigue cracking.

DATES: This AD becomes effective April 3, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of April 3, 2007.
    On August 9, 1996 (61 FR 35122, July 5, 1996), the Director of the 
Federal Register approved the incorporation by reference of Airbus 
Industrie Supplemental Structural Inspection Document, dated September 
1989; and Airbus Industrie A300 Supplemental Structural Inspection 
Document, Revision 2, dated June 1994.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a> or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,

[[Page 8605]]

International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a> 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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 96-13-11, amendment 39-
9679 (61 FR 35122, July 5, 1996). The existing AD applies to all Airbus 
Model A300 B2, B4-100, and B4-200 series airplanes. That NPRM was 
published in the Federal Register on September 26, 2006 (71 FR 56058). 
That NPRM proposed to continue to require supplemental structural 
inspections to detect fatigue cracking, and repair of cracked 
structure. That NPRM also proposed to require revising the maintenance 
program by incorporating new and revised supplemental structural 
inspections, inspection intervals, and repairs; and repair of any 
damaged, cracked, or corroded structure; which would end the existing 
supplement structural inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.

Request for Change to the Applicability

    Airbus, the manufacturer, requests that we exclude the A300-600 
series airplanes from the AD applicability. The commenter refers us to 
page 1-A of Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Issue 3, dated September 2005, as revised by Airbus 
Temporary Revision 3.1, dated April 2006, which does not include A300-
600 series airplanes.
    We agree with the commenter's request. We do not want any reader of 
this AD to infer that A300-600 series airplanes are included, and have 
changed the applicability to exclude those airplanes in paragraph (c) 
of this AD.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the change described previously. 
We have determined that this change will neither increase the economic 
burden on any operator nor increase the scope of the AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          Number of U.S.-
                     Action                         Work     Average labor              Parts                Cost per       registered      Fleet cost
                                                   hours     rate per hour                                   airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Implementation of supplemental structural              597             $80  None........................         $47,760              29      $1,385,040
 inspection program (required by AD 96-13-11).
Revision of the FAA-approved maintenance                10              80  None........................             800              29          23,200
 program (new action).
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-9679 (61 FR 35122, July 5, 1996) and by adding 
the following new airworthiness directive (AD):

2007-04-11 Airbus: Amendment 39-14943. Docket No. FAA-2006-25890; 
Directorate Identifier 2006-NM-115-AD.

Effective Date

    (a) This AD becomes effective April 3, 2007.

[[Page 8606]]

Affected ADs

    (b) This AD supersedes AD 96-13-11.

Applicability

    (c) This AD applies to all Airbus Model A300 B2 and B4 series 
airplanes, certificated in any category, excluding A300-600 series 
airplanes.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (x) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued damage tolerance of the affected structure. The FAA 
has provided guidance for this determination in Advisory Circular 
(AC) 25-1529.

Unsafe Condition

    (d) This AD results from a review of service history and reports 
received from the current supplemental structural inspection 
document program. We are issuing this AD to prevent reduced 
structural integrity of these airplanes due to fatigue cracking.

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 96-13-11

    (f) Within one year after March 9, 1993 (the effective date of 
AD 93-01-24, amendment 39-8478), incorporate a revision into the 
FAA-approved maintenance inspection program that provides for 
supplemental maintenance inspections, modifications, repair, or 
replacement of the significant structural details (SSD) and 
significant structural items (SSI) specified in ``Airbus Industrie 
A300 Supplemental Structural Inspection Document'' (SSID), dated 
September 1989 (hereafter referred to as ``the SSID'').
    (g) Within one year after August 9, 1996 (the effective date of 
AD 96-13-11), replace the revision of the FAA-approved maintenance 
program required by paragraph (f) of this AD with the inspections, 
inspection intervals, repairs, and replacements defined in ``Airbus 
Industrie A300 Supplemental Structural Inspection Document'' (SSID), 
Revision 2, dated June 1994 (hereafter referred to as ``Revision 2 
of the SSID''). Accomplish the actions specified in the service 
bulletins identified in Section 6, ``SB Reference List,'' Revision 2 
of the SSID, at the times specified in those service bulletins. The 
actions are to be accomplished in accordance with those service 
bulletins.
    (1) For airplanes that have exceeded the threshold specified in 
any of the service bulletins identified in Section 6, ``SB Reference 
List,'' Revision 2 of the SSID: Accomplish the actions specified in 
those service bulletins within the grace period specified in that 
service bulletin. The grace period is to be measured from August 9, 
1996.
    (2) For airplanes that have exceeded the threshold specified in 
any of the service bulletins identified in Section 6, ``SB Reference 
List,'' Revision 2 of the SSID, and a grace period is not specified 
in that service bulletin: Accomplish the actions specified in that 
service bulletin within 1,500 flight cycles after August 9, 1996.
    (h) If any cracked structure is detected during the inspections 
required by either paragraph (f) or (g) of this AD, prior to further 
flight, permanently repair the cracked structure in accordance with 
either paragraph (h)(1), (h)(2), or (h)(3) of this AD.

    Note 2: A permanent repair is defined as a repair that meets the 
certification basis of the airplane, and does not require additional 
modification at a later date.

    (1) The service bulletins listed in Section 6, ``SB Reference 
List,'' of the SSID (for airplanes that are currently being 
inspected in accordance with paragraph (f) of this AD); or in 
accordance with a method approved by the Manager, International 
Branch, ANM-116 (formerly the Standardization Branch, ANM-113), FAA, 
Transport Airplane Directorate, if a permanent repair is not 
specified in any of these service bulletins. Or
    (2) The service bulletins listed in Section 6, ``SB Reference 
List,'' of Revision 2 of the SSID (for airplanes that are currently 
being inspected in accordance with paragraph (g) of this AD); or in 
accordance with a method approved by the Manager, International 
Branch, ANM-116 (formerly the Standardization Branch, ANM-113), if a 
permanent repair is not specified in any of these service bulletins. 
Or,
    (3) Other permanent repair data meeting the certification basis 
of the airplane which is approved by the Manager, International 
Branch, ANM-116 (formerly the Standardization Branch, ANM-113); or 
by the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) 
of France.
    (i) For airplanes identified as Fleet Leader Program (FLP) in 
Section 5, ``Fleet Leader Program,'' of the SSID or Revision 2 of 
the SSID: Inspect according to the instructions and intervals 
specified in paragraph 4.4, ``Adjustment of Inspection Requirements 
and DSG,'' of Section 4, or Section 9, as applicable, of the SSID 
(for airplanes inspected in accordance with paragraph (f) of this 
AD), or Revision 2 of the SSID (for airplanes inspected in 
accordance with paragraph (g) of this AD), for each SSD.
    (j) For the purpose of accomplishing paragraphs (i), (k), (l), 
and (n) of this AD, operators shall not use paragraph 6.2, 
``Complete RR Method,'' of Section 9 of the SSID to calculate 
inspection thresholds and intervals.
    (k) For Model A300-B2 and B2K-3C series airplanes: For any SSD 
that has exceeded the values of the threshold specified in paragraph 
6, ``Inspection Threshold and Intervals,'' Section 9 of the SSID, 
inspect at the time specified in either paragraph (k)(1) or (k)(2) 
of this AD, as applicable.
    (1) For airplanes inspected in accordance with paragraph (f) of 
this AD: Inspect within 2,000 landings after March 9, 1993, in 
accordance with the SSID. Or,
    (2) For airplanes inspected in accordance with paragraph (g) of 
this AD: Inspect within 2,000 landings after August 9, 1996, in 
accordance with Revision 2 of the SSID.
    (l) For Model A300-B4 series airplanes: For any SSD that has 
exceeded the values of the threshold specified in paragraph 6, 
``Inspection Threshold and Intervals,'' Section 9 of the SSID, 
inspect at the time specified in either paragraph (l)(1) or (l)(2) 
of this AD, as applicable.
    (1) For airplanes inspected in accordance with paragraph (f) of 
this AD: Inspect within 1,500 landings after March 9, 1993 [the 
effective date of AD 93-01-24, amendment 39-8478]. Or,
    (2) For airplanes inspected in accordance with paragraph (g) of 
this AD: Inspect within 1,500 landings after August 9, 1996.
    (m) For airplanes identified as FLP in Section 5, ``Fleet Leader 
Program,'' of the SSID or Revision 2 of the SSID: Within one year 
after August 9, 1996, apply the basic requirements given in Revision 
2 of the SSID.
    (n) For airplanes that are subject to the requirements of 
paragraph (g) of this AD, and have exceeded the initial inspection 
threshold specified in paragraph 4.4, ``Adjustment of Inspection 
Requirements and DSG,'' of Section 4, or paragraph 6, ``Inspection 
Threshold and Intervals,'' of Section 9, for each SSD: Perform the 
initial inspection prior to the accumulation of the number of flight 
cycles specified in paragraph 7, ``Additional Information,'' Section 
9, of Revision 2 of the SSID.

    Note 3: Fatigue ratings are not applicable to these allowances; 
therefore, no adjustment is required.


    Note 4: Paragraph (n) of this AD provides the ``grace'' periods 
for those airplanes that are new to the FLP or that have newly added 
or revised SSID requirements in accordance with paragraph (g) of 
this AD.


    (o) The grace period provided by paragraph (n) of this AD is 
also applicable to the thresholds and/or repeat intervals for each 
SSD for which the inspection interval or threshold was reduced in 
accordance with the requirements of paragraph (g) of this AD.
    (p) For FLP airplanes identified in Section 5, ``Fleet Leader 
Program,'' of the SSID or Revision 2 of the SSID that are listed in 
Section 7, ``SSI Limitation List,'' of the SSID (for airplanes that 
are currently being inspected in accordance with paragraph (f) of 
this AD), or Revision 2 of the SSID (for airplanes that are 
currently being inspected in accordance with paragraph (g) of this 
AD): Inspect at intervals not to exceed the interval specified for 
each SSI, in accordance with the values given in Section 7, ``SSI 
Limitation List,'' of the SSID or Revision 2 of the SSID, as 
applicable.
    (q) For all airplanes: All inspection results, positive or 
negative, must be reported to Airbus in accordance with either 
paragraph (q)(1) or (q)(2) of this AD, as applicable. Information 
collection requirements contained in this regulation have been 
approved by the Office of Management and Budget (OMB) under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C.

[[Page 8607]]

3501 et seq.) and have been assigned OMB Control Number 2120-0056.
    (1) For FLP airplanes, identified in Section 5, ``Fleet Leader 
Program,'' of the SSID or Revision 2 of the SSID: Submit reports in 
accordance with the instructions in paragraph 5.2, ``SSIP Inspection 
Reporting,'' of Section 5, and paragraph 7.1, ``General,'' of 
Section 7 of the SSID (for airplanes that are currently being 
inspected in accordance with paragraph (f) of this AD); or Revision 
2 of the SSID (for airplanes inspected in accordance with paragraph 
(g) of this AD).
    (2) For all airplanes that are subject to Section 6, ``SB 
Reference List,'' of the SSID: Submit reports in accordance with the 
instructions in the applicable service bulletins identified in 
Section 6 of the SSID (for airplanes that are currently being 
inspected in accordance with paragraph (f) of this AD); or Revision 
2 of the SSID (for airplanes that are currently being inspected in 
accordance with paragraph (g) of this AD).

New Requirements of This AD

Revision of the FAA-Approved Maintenance Inspection Program

    (r) Within 12 months after the effective date of this AD, 
replace the revision of the FAA-approved maintenance program 
required by paragraph (g) of this AD with the supplemental 
structural inspections, inspection intervals, and repairs defined in 
Airbus A300 Airworthiness Limitation Items (ALI) Document SEM2/
95A.1090/05, Issue 3, dated September 2005, as revised by Airbus 
Temporary Revision (TR) 3.1, dated April 2006 (hereafter referred to 
as ``Issue 3 of the ALI''). Accomplish the actions specified in 
Issue 3 of the ALI at the times specified in that ALI, except as 
provided by paragraph (s) of this AD. The actions must be 
accomplished in accordance with Issue 3 of the ALI. Accomplishing 
the applicable initial ALI tasks constitutes terminating action for 
the requirements of paragraphs (f) through (q) of this AD.
    (s) For airplanes that have exceeded the threshold or intervals 
specified in Issue 3 of the ALI for the application tolerance on the 
first interval for new and revised requirements and have exceeded 50 
percent of the intervals specified in sections D and E of Issue 3 of 
the ALI: Do the actions within 6 months after the effective date of 
this AD.

Corrective Actions

    (t) Damaged, cracked, or corroded structure detected during any 
inspection done in accordance with Issue 3 of the ALI must be 
repaired, before further flight, in accordance with Issue 3 of the 
ALI, except as provided by paragraph (u) of this AD; or other data 
meeting the certification basis of the airplane which is approved by 
the Manager, International Branch, ANM-116; or by the European 
Aviation Safety Agency (EASA) (or its delegated agent).
    (u) Where Issue 3 of the ALI specifies contacting Airbus for 
appropriate action: Before further flight, repair the damaged, 
cracked, or corroded structure using a method approved by either the 
Manager, International Branch, ANM-116; or the EASA (or its 
delegated agent).

No Fleet Sampling

    (v) Although Issue 3 of the ALI specifies to do a ``Sampling 
Concept'' in section B, this AD prohibits the use of such a sampling 
program and requires all affected airplanes of the fleet to be 
inspected.

No Reporting

    (w) Although Issue 3 of the ALI specifies to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

Alternative Methods of Compliance (AMOCs)

    (x)(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.
    (3) AMOCs approved previously in accordance with AD 96-13-11 are 
approved as AMOCs for the corresponding provisions of paragraphs (f) 
through (q) of this AD.

Related Information

    (y) EASA airworthiness directive 2006-0071, dated March 30, 
2006, also addresses the subject of this AD.

Material Incorporated by Reference

    (z) You must use Airbus A300 Airworthiness Limitation Items 
Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised 
by Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Temporary Revision 3.1, including attachment, dated 
April 2006, and including attachments dated September 2005; Airbus 
Industrie Supplemental Structural Inspection Document, dated 
September 1989; and Airbus Industrie A300 Supplemental Structural 
Inspection Document, Revision 2, dated June 1994; as applicable, to 
perform the actions that are required by this AD, unless the AD 
specifies otherwise. Airbus A300 Airworthiness Limitation Items 
Document SEM2/95A.1090/05, Issue 3, dated September 2005, contains 
the following effective pages:

------------------------------------------------------------------------
                                  Issue number shown
           Page number                  on page       Date shown on page
------------------------------------------------------------------------
1-SOC--10-SOC...................  Section SOC, 3....  September 2005.
1-TOC...........................  Section TOC, 3....  September 2005.
1-A.............................  Section A, 3......  September 2005.
1-B--6-B........................  Section B, 3......  September 2005.
1-C, 2..........................  Section C, 3......  September 2005.
1-D, 2-D, 3-101.................  Section D, 3......  September 2005.
1-E, 1-24.......................  Section E, 3......  September 2005.
1-F, 2-39.......................  Section F, 3......  September 2005.
1-G, 20-G, 30-G, 101-G..........  Section G, 3......  September 2005.
2-G--19-G, 21-G--29-G, 31-G--     1.................  January 2004.
 100G, 102-G--328-G.
1-App--3-App....................  Section App, 3....  September 2005.
------------------------------------------------------------------------

    (Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Issue 3, dated September 2005, contains two page 1-SOC 
and two page 190-G. The first page identified as 1-SOC is the Record 
of Changes and the second page 1-SOC is the first page of the 
Summary of Changes. The first page identified as page 190-G refers 
to Airworthiness Limitation Item 546014, and the second page 190-G 
refers to Airworthiness Limitation Item 556001.) Airbus A300 
Airworthiness Limitations Items Document SEM2/95A.1090/05, Temporary 
Revision 3.1, dated April 2006, contains the following effective 
pages:

------------------------------------------------------------------------
                                  Issue number shown
           Page number                  on page       Date shown on page
------------------------------------------------------------------------
1-T.R. 3.1-4-T.R.3.1............  Original..........  April 2006.
Section D, 3-27.................  T.R.3.1...........  April 2006.
Section E, 1-4..................  3.................  September 2005.
Section F, 2-6..................  3.................  September 2005.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of Airbus A300 Airworthiness Limitation 
Items Document SEM2/95A.1090/05, Issue 3, dated September 2005; as 
revised by Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Temporary Revision 3.1, including attachment, dated 
April 2006, and including attachments, dated September 2005; in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On August 9, 1996 (61 FR 35122, July 5, 1996), the Director 
of the Federal Register approved the incorporation by reference of 
Airbus Industrie Supplemental Structural Inspection Document, dated 
September 1989; and Airbus Industrie Supplemental Structural 
Inspection Document, Revision 2, dated June 1994.
    (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal--register/

[[Page 8608]]

code--of--federal--regulations/ibr--locations.html.

    Issued in Renton, Washington, on February 6, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-2512 Filed 2-26-07; 8:45 am]
BILLING CODE 4910-13-P