Document ID: FAA-2012-0488-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2012-05-22T04:00Z

[Federal Register Volume 77, Number 99 (Tuesday, May 22, 2012)]
[Proposed Rules]
[Pages 30228-30230]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-12339]

[[Page 30228]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0488; Directorate Identifier 2011-NM-106-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A300 B4-600 and A300 B4-600R, Model A300, and 
Model A310 series airplanes. This proposed AD was prompted by reports 
of fatigue cracking in the crossbeams at the junction of the actuator 
beam of the lower deck cargo door. This proposed AD would require 
repetitive inspections of the crossbeams of certain fuselage frames, 
and repair if necessary. We are proposing this AD to detect and correct 
cracking of the crossbeams at the junction of the actuator beam of the 
lower deck cargo door, which could result in failure to withstand 
ultimate load conditions, and consequent reduced structural integrity 
of the airplane.

DATES: We must receive comments on this proposed AD by July 6, 2012.

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 W12-140, 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; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0488; 
Directorate Identifier 2011-NM-106-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

    The European Aviation Safety Agency (EASA), which is the aviation 
authority for the Member States of the European Community, has issued 
EASA Airworthiness Directive 2011-0086, dated May 12, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Some operators have reported cracked crossbeams at the junction 
with the lower deck cargo door actuator beam. The investigation 
results indicate that these cracks initiated in the fastener hole, 
propagated in a vertical direction and were due to fatigue.
    This condition, if not corrected, could lead, in case of cracks 
propagation in a crossbeam (upper and lower web), to the floor grid 
being unable to withstand ultimate load condition.
    For the reasons described above, this [EASA] AD requires 
repetitive [high frequency eddy current] inspections [for cracks] of 
certain crossbeams including those previously repaired by the 
Structure Repair Manual (SRM) or Repair Approval Sheet (RAS).

    The required actions include repairing any cracking. As an option, 
modifying the crossbeams terminates the repetitive inspections. You may 
obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued the following Service Bulletins:
     A300-53-0389, Revision 02, dated April 27, 2011;
     A310-53-2133, Revision 02, dated April 27, 2011; and
     A300-53-6166, Revision 01, dated May 21, 2010.
    Airbus has also issued the following Mandatory Service Bulletins:
     A300-53-0390, dated January 15, 2010;
     A310-53-2134, dated January 15, 2010; and
     A300-53-6168, dated January 15, 2010.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

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

Differences Between This Proposed AD and the MCAI or Service 
Information

    Where the service information identified in the ``Relevant Service 
Information'' section specifies to contact the manufacturer for 
instructions on certain cracking conditions, this proposed AD would 
require repairing those conditions using a method approved by the FAA 
or EASA (or its delegated agent). In light of the type of repair that 
would be required to address the unsafe condition, and consistent

[[Page 30229]]

with existing bilateral airworthiness agreements, we have determined 
that, for this proposed AD, a repair approved by the FAA or the EASA 
(or its delegated agent) would be acceptable for compliance with this 
proposed AD.
    Although the MCAI allows further flight after cracks are found 
during compliance with the required action, this proposed AD would 
require repair of any cracked/damaged frames before further flight. 
This difference has been coordinated with the EASA.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 152 products of U.S. registry. We also estimate that 
it would take about 1 work-hour per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $12,920, or $85 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 adding the following new AD:

The Boeing Company: Docket No. FAA-2012-0488; Directorate Identifier 
2011-NM-106-AD.

(a) Comments Due Date

    We must receive comments by July 6, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203; Model A300 B4-601, B4-603, B4-620, 
and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; and 
Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes; certificated in any category; except those identified in 
paragraph (c)(1), (c)(2), or (c)(3) of this AD, as applicable.
    (1) Airplanes on which Airbus Service Bulletin A300-53-6166 
(Airbus Modification 13434) has been embodied in service (for Model 
A300 B4-600 and A300 B4-600R series airplanes).
    (2) Airplanes on which Airbus Service Bulletin A300-53-0389 
(Airbus Modification 13434) has been embodied in service (for Model 
A300 series airplanes).
    (3) Airplanes on which Airbus Service Bulletin A310-53-2133 
(Airbus Modification 13434) has been embodied in service (for Model 
A310 series airplanes).

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fatigue cracking in the 
crossbeams at the junction of the actuator beam of the lower deck 
cargo door. We are issuing this AD to detect and correct cracking of 
the crossbeams at the junction of actuator beam of the lower deck 
cargo door, which could result in failure to withstand ultimate load 
conditions, and consequent reduced structural integrity of the 
airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Repetitive High Frequency Eddy Current Inspections

    (1) For airplanes on which the crossbeams at frames (FR) 22/23 
and FR 61/62 have not been repaired as specified in an Airbus 
structural repair manual or repair approval sheet as of the 
effective date of this AD: Before the accumulation of 10,000 total 
flight cycles since first flight of the airplane, or within 600 
flight cycles after the effective date of this AD, whichever occurs 
later; perform a high frequency eddy current (HFEC) inspection for 
cracking of the crossbeam fuselage frame stations FR 22/23 and FR 
61/62, in accordance with the Accomplishment Instructions of the 
applicable service bulletin identified in paragraph (g)(1)(i), 
(g)(1)(ii), or (g)(1)(iii) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 600 flight cycles until the 
modification specified in paragraph (i) of this AD has been done.
    (i) Airbus Mandatory Service Bulletin A300-53-0390, dated 
January 15, 2010 (for Model A300 series airplanes).
    (ii) Airbus Mandatory Service Bulletin A310-53-2134, dated 
January 15, 2010 (for Model A310 series airplanes).
    (iii) Airbus Mandatory Service Bulletin A300-53-6168, dated 
January 15, 2010 (for Model A300-600 series airplanes).
    (2) For airplanes on which the crossbeams at FR 22/23 and FR 61/
62 have been repaired as specified in an Airbus structural repair 
manual or repair approval sheet as of the effective date of this AD: 
Before the accumulation of 10,000 total flight cycles since first 
flight of the airplane, or within 600 flight cycles after the 
effective date of this AD, whichever occurs later; repair in 
accordance with 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).

(h) Corrective Action

    If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight repair any crack 
using a method approved by the Manager, International Branch, ANM-
116; or EASA (or its delegated agent).

[[Page 30230]]

(i) Optional Terminating Action

    Modifying the crossbeam fuselage frame stations FR 22/23 and FR 
61/62, including doing rotating probe inspections for cracks of 
fastener holes in accordance with the Accomplishment Instructions of 
the applicable service bulletin identified in paragraph (i)(1), 
(i)(2), or (i)(3) of this AD, and repairing any crack using a method 
approved by the Manager, International Branch, ANM-116; or EASA (or 
its delegated agent), terminates the repetitive inspections required 
by paragraph (g)(1) of this AD.
    (1) Airbus Service Bulletin A300-53-0389, Revision 02, dated 
April 27, 2011 (for Model A300 series airplanes).
    (2) Airbus Service Bulletin A310-53-2133, Revision 02, dated 
April 27, 2011 (for Model A310 series airplanes).
    (3) Airbus Service Bulletin A300-53-6166, Revision 01, dated May 
21, 2010 (for Model A300-600 series airplanes).

(j) Other FAA AD Provisions

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

(k) Related Information

    Refer to EASA Airworthiness Directive 2011-0086, dated May 12, 
2011; and the applicable service bulletin identified in paragraphs 
(k)(1), (k)(2), (k)(3), (k)(4), (k)(5), and (k)(6) of this AD for 
related information.
    (1) Airbus Service Bulletin A300-53-0389, Revision 02, dated 
April 27, 2011.
    (2) Airbus Service Bulletin A310-53-2133, Revision 02, dated 
April 27, 2011.
    (3) Airbus Service Bulletin A300-53-6166, Revision 01, dated May 
21, 2010. (4) Airbus Mandatory Service Bulletin A300-53-0390, dated 
January 15, 2010.
    (5) Airbus Mandatory Service Bulletin A310-53-2134, dated 
January 15, 2010.
    (6) Airbus Mandatory Service Bulletin A300-53-6168, dated 
January 15, 2010.

    Issued in Renton, Washington, on May 10, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-12339 Filed 5-21-12; 8:45 am]
BILLING CODE 4910-13-P