Document ID: FAA-2009-0431-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Airbus Model A310-203 and -222 Airplanes and Model A300 B4-620 Airplanes
Posted Date: 2009-05-07T04:00Z

[Federal Register: May 7, 2009 (Volume 74, Number 87)]
[Proposed Rules]               
[Page 21274-21278]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07my09-14]                         

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================

[[Page 21274]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0431; Directorate Identifier 2007-NM-174-AD]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A310-203 and -222 
Airplanes and Model A300 B4-620 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

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:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03, 
amendment 39-5871] was issued to prevent development of damage, 
which was discovered during [a] fatigue test in the attachment 
angles of the rear pressure bulkhead (fuselage frame 80/82).
    Following the life extension activities linked to the A310 
program, the interval of inspection for A310-200 aircraft series was 
reduced from 12000 flight cycles (FC) to 9000 FC * * *.
    Some stress analysis conducted in the frame of the life 
extension activities of the A300-600 program leads the manufacturer 
to reduce as well the interval of inspection applicable to A300B4-
620 and A300C4-620 aircraft models.

The unsafe condition is cracking in the attachment angles of the rear 
pressure bulkhead, which could result in failure of the rear pressure 
bulkhead. 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 8, 2009.

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 or 425-227-1152.

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: Tom Stafford, Aerospace Engineer, 
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:

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-2009-0431; 
Directorate Identifier 2007-NM-174-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 March 3, 1988, we issued AD 88-06-03, Amendment 39-5871 (53 FR 
7730, March 10, 1988). That AD required actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 88-06-03, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, advised that, due to life extension activities 
linked to the A310 program and stress analysis conducted in the frame 
of the life extension activities of the A300-600 program, the 
repetitive inspection interval for the attachment angles of the rear 
pressure bulkhead has been reduced from 12,000 flight cycles to 9,000 
flight cycles for Model A310-203 and -222 airplanes and Model A300 B4-
620 airplanes.
    EASA has issued Airworthiness Directive 2007-0297R1, dated 
September 17, 2008 (referred to after this as ``the MCAI''), to correct 
an unsafe condition for the specified products. The MCAI states:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03] was 
issued to prevent development of damage, which was discovered during 
[a] fatigue test in the attachment angles of the rear pressure 
bulkhead (fuselage frame 80/82).
    Following the life extension activities linked to the A310 
program, the interval of inspection for A310-200 aircraft series was 
reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the 
issuance of EASA

[[Page 21275]]

AD 2007-0157, superseding DGAC France AD 86-102-74(B).
    Some stress analysis conducted in the frame of the life 
extension activities of the A300-600 program leads the manufacturer 
to reduce as well the interval of inspection applicable to A300B4-
620 and A300C4-620 aircraft models.
    EASA AD 2007-02977 superseded EASA AD 2007-0157, retaining for 
A310 aircraft the requirements of EASA AD 2007-0157 and requiring 
the application of Airbus Service Bulletin (SB) A300-53-6005 
Revision 4 on Airbus A300-600 aircraft, reducing the inspection 
interval from 12000 FC to 9000 FC.
    [EASA] AD [2007-0297] has been revised to remove an 
inappropriate reference regarding the normal inspection program from 
the Compliance section, Note 3.

    The unsafe condition is cracking in the attachment angles of the 
rear pressure bulkhead, which could result in failure of the rear 
pressure bulkhead. The required actions include a modification of the 
rear pressure bulkhead to improve the fatigue life of the attachment 
angles at frame (FR) 80/82, and, for certain airplanes, repetitive 
inspections for cracks in the rear pressure bulkhead and repair if 
necessary.
    The modification includes installing additional attachment angles 
on the circumference of FR 80/82; installing a filler; installing 
additional supports between the aft pressure bulkhead and FR 80/82; 
installing an additional frame stiffener and support between the aft 
pressure bulkhead and FR 79 at stringer (STGR) 13; modifying the aft 
lavatories; applying surface protection to the modified area of the aft 
pressure bulkhead; modifying, reidentifying, and installing the heat 
and sound insulation in the area of STGR 9 and STGR 13 and between FR 
79 and FR 80/82, left and right; and for certain airplanes, doing 
related investigative and corrective actions if necessary.
    The related investigative action is doing a visual inspection 
around the entire circumference between FR 80/82 and the aft pressure 
bulkhead for damaged filler. The corrective action is removing any 
damaged filler and the adjacent area around the damage.
    We have removed Airbus Model A310-221 airplanes having serial 
numbers 295 and 0306 from the applicability of this proposed AD. The 
MCAI does not include Airbus Model A310-221 in its applicability as it 
has been determined that those airplanes are not subject to the 
identified unsafe condition addressed by the relevant service 
information listed below. However, those airplanes are subject to 
certain other actions required by AD 2006-22-03, amendment 39-14800 (71 
FR 62890, October 27, 2006), as specified in the ``Other Relevant 
Rulemaking'' paragraph below.
    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued the following service bulletins:
     Airbus Service Bulletin A310-53-2024, Revision 05, dated 
October 13, 2006.
     Airbus Service Bulletin A310-53-2025, Revision 06, dated 
August 3, 2006.
     Airbus Service Bulletin A300-53-6005, Revision 04, dated 
July 18, 2007.
     Airbus Service Bulletin A300-53-6006, Revision 3, dated 
March 24, 1989.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

Other Relevant Rulemaking

    We issued AD 2006-22-03 to prevent corrosion on the inner rim angle 
and cleat profile splice of the aft pressure bulkhead. That AD applies 
to Airbus Model A310 and A300-600 series airplanes, except airplanes on 
which Airbus Modification 6788 has been incorporated in production. 
That AD requires modification of the aft pressure bulkhead for improved 
corrosion protection and drainage, and a related concurrent action.
    The related concurrent action specified in paragraph (h) of AD 
2006-22-03 is a modification of the aft pressure bulkhead in accordance 
with Airbus Service Bulletin A310-53-2025, Revision 06, dated August 3, 
2006, and Airbus Service Bulletin A300-53-6006, Revision 3, dated March 
24, 1989, as applicable (which is the same modification that this NPRM 
would require). The compliance time to do the modification specified in 
paragraph (h) of AD 2006-22-03 is prior to or concurrent with the 
actions specified in paragraph (g) of AD 2006-22-03; the compliance 
time for paragraph (g) of AD 2006-22-03 is within 60 months after 
December 1, 2006 (the effective date of AD 2006-22-03). This NPRM would 
supersede AD 2006-22-03 to require that the modification of the aft 
pressure bulkhead be done before the accumulation of 12,000 total 
flight cycles since first flight, or within 1,500 flight cycles, 
whichever occurs later.
    Certain airplanes affected by AD 2006-22-03 are also affected by 
this NPRM, and therefore, the requirements of this NPRM would 
necessitate that some operators do the modification required by 
paragraph (h) of AD 2006-22-03 early. Accomplishing the modification 
within the compliance time specified in paragraph (f)(2) of this NPRM 
is necessary to address cracking in the attachment angles of the rear 
pressure bulkhead, which could result in failure of the rear pressure 
bulkhead.

Other Corrosion and Fatigue ADs

    Operators should note that we have also issued other ADs that 
involve work in the area of the aft pressure bulkhead. We issued those 
ADs to address unsafe conditions related to either corrosion or fatigue 
in the aft pressure bulkhead. The following table, titled ``Other 
relevant rulemaking,'' provides an overview of all those issued ADs.

                                        Table--Other Relevant Rulemaking
----------------------------------------------------------------------------------------------------------------
                                       Refers to Airbus Service
                AD--                          Bulletin--                Requiring--            Addressing--
----------------------------------------------------------------------------------------------------------------
88-06-03 (would be superseded by     A310-53-2024, Revision 1,    Repetitive inspections  Fatigue.
 this proposed AD).                   dated June 20, 1986; and
                                      Revision 3, February 17,
                                      1987.
                                     A310-53-2025, original       Modification..........  Fatigue.
                                      issue, dated April 21,
                                      1986; and Revision 3,
                                      April 7, 1987.
98-19-22, amendment 39-10763 (63 FR  A300-53-6066, dated October  Repetitive inspections  Corrosion.
 49656, September 17, 1998)           16, 1996; and Revision 01,
 (superseded by AD 2005-26-16).       dated March 11, 1998.
                                     A310-53-2092, dated October  Repetitive inspections  Corrosion.
                                      16, 1996; and Revision 01,
                                      dated March 11, 1998.
2005-26-16, amendment 39-14437 (70   A300-53-6136, Revision 01,   Repetitive inspections  Corrosion.
 FR 77307, December 30, 2005).        dated July 18, 2005.
                                     A310-53-2114, Revision 01,   Repetitive inspections  Corrosion.
                                      dated September 1, 2005.

[[Page 21276]]

2006-22-03, amendment 39-14800 (71   A300-53-6017, Revision 02,   Modification..........  Corrosion.
 FR 62890, October 27, 2006).         dated February 25, 2004.
                                     A310-53-2036, Revision 02,   Modification..........  Corrosion.
                                      dated February 25, 2004.
                                     A300-53-6006, Revision 3,    Modification..........  Fatigue.
                                      March 24, 1989.
                                     A310-53-2025, Revision 06,   Modification..........  Fatigue.
                                      August 3, 2006.
----------------------------------------------------------------------------------------------------------------

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 32 products of U.S. registry. We also estimate that 
it would take 668 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Required parts would cost about $15,322 per product. Where 
the service information lists required parts costs that are covered 
under warranty, we have assumed that there will be no charge for these 
costs. As we do not control warranty coverage for affected parties, 
some parties may incur costs higher than estimated here. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be $2,200,384, or $68,762 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 39-5871 (53 FR 
7730, March 10, 1988) and adding the following new AD:

Airbus: Docket No. FAA-2009-0431; Directorate Identifier 2007-NM-
174-AD.

Comments Due Date

    (a) We must receive comments by June 8, 2009.

Affected ADs

    (b) The proposed AD supersedes AD 88-06-03, Amendment 39-5871.

Applicability

    (c) This AD applies to Airbus Model A310-203 and -222 airplanes, 
and Model A300 B4-620 airplanes; certificated in any category; all 
serial numbers except airplanes on which Airbus Modification 05526 
has been incorporated in production.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    DGAC (Direction G[eacute]n[eacute]rale de l'Aviation Civile) 
France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03, 
amendment 39-5871] was issued to prevent development of damage, 
which was discovered during [a] fatigue test in the attachment 
angles of the rear pressure bulkhead (fuselage frame 80/82).
    Following the life extension activities linked to the A310 
program, the interval of inspection for A310-200 aircraft series was 
reduced from 12000 flight cycles (FC) to 9000 FC, which prompted the 
issuance of EASA AD 2007-0157, superseding DGAC France AD 86-102-
74(B).
    Some stress analysis conducted in the frame of the life 
extension activities of the A300-600 program leads the manufacturer 
to

[[Page 21277]]

reduce as well the interval of inspection applicable to A300B4-620 
and A300C4-620 aircraft models.
    EASA AD 2007-0297 superseded EASA AD 2007-0157, retaining for 
A310 aircraft the requirements of EASA AD 2007-0157 and requiring 
the application of Airbus Service Bulletin (SB) A300-53-6005 
Revision 4 on Airbus A300-600 aircraft, reducing the inspection 
interval from 12000 FC to 9000 FC.
    [EASA] AD [2007-0297] has been revised to remove an 
inappropriate reference regarding the normal inspection program from 
the Compliance section, Note 3.
    The unsafe condition is cracking in the attachment angles of the 
rear pressure bulkhead, which could result in failure of the rear 
pressure bulkhead. The required actions include a modification of 
the rear pressure bulkhead to improve the fatigue life of the 
attachment angles at frame (FR) 80/82; applicable related 
investigative and corrective actions; and, for certain airplanes, 
repetitive inspections for cracks in the rear pressure bulkhead and 
repair if necessary.

Requirements of This AD: Actions and Compliance

    (f) Unless already done, do the following actions.

Modification

    (1) Except as required by paragraph (f)(2) of this AD: Before 
the accumulation of 12,000 total flight cycles since first flight, 
or within 1,500 flight cycles after the effective date of this AD, 
whichever occurs later, modify the aft pressure bulkhead to improve 
the fatigue life of the attachment angles at frame 80/82 and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6006, Revision 3, dated March 24, 1989; or Airbus 
Service Bulletin A310-53-2025, Revision 06, dated August 3, 2006; as 
applicable. Do all applicable related investigative and corrective 
actions before further flight.
    (2) For airplanes identified in paragraph (c) of AD 2006-22-03, 
amendment 39-14800: At the earlier of the compliance times specified 
in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, do the actions 
specified in paragraph (f)(1) of this AD.
    (i) Before the accumulation of 12,000 total flight cycles since 
first flight, or within 1,500 flight cycles after the effective date 
of this AD, whichever occurs later.
    (ii) At the compliance time specified in paragraph (h) of AD 
2006-22-03.

Inspections and Corrective Action

    (3) For airplanes on which the modification required by 
paragraph (f)(1) or (f)(2) of this AD is done after the accumulation 
of 6,000 total flight cycles since first flight: At the times 
specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, do an 
eddy current inspection for any cracking in the critical area of the 
rear pressure bulkhead between stringers 8 and 18, and repair all 
cracking before further flight, in accordance with the 
Accomplishment Instructions of Airbus A300-53-6005, Revision 04, 
dated July 18, 2007; or Airbus Service Bulletin A310-53-2024, 
Revision 05, dated October 13, 2006; as applicable.
    (i) Before or concurrently with the modification required by 
paragraph (f)(1) or (f)(2) of this AD, as applicable; and
    (ii) Before the accumulation of 18,000 total flight cycles since 
first flight, or within 1,500 flight cycles after the effective date 
of this AD, whichever occurs later; and thereafter at intervals not 
to exceed 9,000 flight cycles.
    (4) For airplanes on which the modification required by 
paragraph (f)(1) or (f)(2) of this AD is done at or before the 
accumulation of 6,000 total flight cycles since first flight: Before 
the accumulation of 18,000 total flight cycles since first flight, 
or within 1,500 flight cycles after the effective date of this AD, 
whichever occurs later, do an eddy current inspection for any 
cracking in the critical area of the rear pressure bulkhead between 
stringers 8 and 18, and repair all cracking before further flight, 
in accordance with the Accomplishment Instructions of Airbus A300-
53-6005, Revision 04, dated July 18, 2007; or Airbus Service 
Bulletin A310-53-2024, Revision 05, dated October 13, 2006; as 
applicable. Repeat the inspection thereafter at intervals not to 
exceed 9,000 flight cycles.
    (5) Modifications done before the effective date of this AD in 
accordance with the service bulletins identified in Table 1 of this 
AD are acceptable for compliance with the requirements of paragraph 
(f)(1) and (f)(2) of this AD.

                          Table 1--Modifications Done Using Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                     Airbus Service
              Model                     Bulletin            Revision                       Dated
----------------------------------------------------------------------------------------------------------------
A300 B4-620 airplanes............       A300-53-6006  Original...........  May 6, 1986.
                                        A300-53-6006  1..................  September 19, 1986.
                                        A300-53-6006  2..................  August 11, 1988.
A310-203 and -222 airplanes......       A310-53-2025  Original...........  April 21, 1986.
                                        A310-53-2025  1..................  September 19, 1986.
                                        A310-53-2025  2..................  February 16, 1987.
                                        A310-53-2025  3..................  April 7, 1987.
                                        A310-53-2025  4..................  October 20, 1987.
                                        A310-53-2025  5..................  March 24, 1989.
----------------------------------------------------------------------------------------------------------------

    (6) Inspections done before the effective date of this AD in 
accordance with the service bulletins identified in Table 2 of this 
AD are acceptable for compliance with the requirements of paragraph 
(f)(3) of this AD.

                            Table 2--Inspections Done With Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                     Airbus Service
              Model                     Bulletin            Revision                       Dated
----------------------------------------------------------------------------------------------------------------
A300 B4-620 airplanes............       A300-53-6005  Original...........  May 6, 1986.
                                        A300-53-6005  1..................  June 20, 1986.
                                        A300-53-6005  2..................  September 22, 1986.
                                        A300-53-6005  3..................  April 22, 1987.
A310-203 and -222 airplanes......       A310-53-2024  Original...........  April 21, 1986.
                                        A310-53-2024  1..................  June 20, 1986.
                                        A310-53-2024  2..................  October 2, 1986.
                                        A310-53-2024  3..................  February 17, 1987.
                                        A310-53-2024  4..................  February 2, 1988.
----------------------------------------------------------------------------------------------------------------

[[Page 21278]]

    (7) Modification of the aft pressure bulkhead to improve the 
fatigue life of the attachment angles at frame (FR) 80/82 in 
accordance with paragraph (h) of AD 2006-22-03, is acceptable for 
compliance with the corresponding requirement of paragraphs (f)(1) 
and (f)(2) of this AD.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: This AD includes a compliance time specified in 
paragraph (f)(2) of this AD for airplanes that are also affected by 
AD 2006-22-03. We realize that the requirements of this AD will 
necessitate that some operators do the modification required by 
paragraph (h) of AD 2006-22-03 early. However, accomplishing the 
modification within the compliance time specified in this AD is 
required to address cracking in the attachment angles of the rear 
pressure bulkhead, which could result in failure of the rear 
pressure bulkhead.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to ATTN: Tom 
Stafford, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1622; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office.
    (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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI EASA Airworthiness Directive 2007-0297R1, 
dated September 17, 2008, and the service bulletins listed in Table 
3 of this AD, for related information.

                                       Table 3--Related Service Bulletins
----------------------------------------------------------------------------------------------------------------
            Airbus Service Bulletin                   Revision                          Date
----------------------------------------------------------------------------------------------------------------
A310[dash]53[dash]2024.........................                 05  October 13, 2006.
A310[dash]53[dash]2025.........................                 06  August 3, 2006.
A300[dash]53[dash]6005.........................                 04  July 18, 2007.
A300[dash]53[dash]6006.........................                  3  March 24, 1989.
----------------------------------------------------------------------------------------------------------------

    Issued in Renton, Washington, on May 1, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-10614 Filed 5-6-09; 8:45 am]

BILLING CODE 4910-13-P