[Federal Register Volume 73, Number 14 (Tuesday, January 22, 2008)]
[Proposed Rules]
[Pages 3656-3659]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-977]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0048; Directorate Identifier 2007-NM-276-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 and A300-600 Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

    Based on some recent in-service findings for fluid ingress and/
or inner skin disbond damage on rudders, AIRBUS decided to introduce 
some further structural inspections to specific rudder areas. This 
type of damage could result in reduced structural integrity of the 
rudder.
* * * * *
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 February 21, 
2008.

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.

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-2008-0048; 
Directorate Identifier 2007-NM-276-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory,

[[Page 3657]]

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 24, 2006, we issued AD 2006-07-13, Amendment 39-14540 (71 
FR 16030, March 30, 2006), to require one-time inspections of the 
rudder for discrepancies, and corrective action if necessary. That AD 
required actions intended to address an unsafe condition on the 
products listed above.
    Since we issued AD 2006-07-13, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has issued EASA Airworthiness Directive 2007-0266, 
dated October 8, 2007 (referred to after this as ``the MCAI''), to 
correct an unsafe condition for the specified products. The MCAI 
states:

    Based on some recent in-service findings for fluid ingress and/
or inner skin disbond damage on rudders, AIRBUS decided to introduce 
some further structural inspections to specific rudder areas. This 
type of damage could result in reduced structural integrity of the 
rudder.
    For the reasons stated above, this AD requires the 
accomplishment of a thorough inspection program [a one-time 
inspection and repetitive inspections for damage of the rudder] by 
ultrasonic and/or t[h]ermographic methods, compared to the 
inspections already required by Airworthiness Directive (AD) 2006-
0066, issued on 24 March 2006 [which corresponds to FAA AD 2006-07-
13] as a precautionary measure, in order to verify the structural 
integrity of the rudder.
* * * * *
The corrective actions include reporting both positive and negative 
findings to Airbus, doing a temporary repair, and contacting Airbus for 
repair instructions and doing a permanent repair. The compliance times 
for doing the repairs range from before further flight to within 4,500 
flight cycles after doing the inspection, depending on the inspection 
type and the configuration of the airplane. The repetitive inspection 
intervals range from 1,200 flight cycles to 5,000 flight cycles, 
depending on the inspection type and the configuration of the airplane. 
You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued the following service bulletins:
     A300-55-6043, Revision 01, dated December 3, 2007
     A300-55-6044, Revision 01, dated December 20, 2007
     A310-55-2044, Revision 01, dated December 3, 2007
     A310-55-2045, Revision 01, dated December 20, 2007
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

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

Differences Between This AD and the MCAI or Service Information

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

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 123 products of U.S. registry. We also estimate that 
it would take about 22 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $216,480, or $1,760 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, 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 39-14540 (71 FR

[[Page 3658]]

16030, March 30, 2006) and adding the following new AD:

Airbus: Docket No. FAA-2008-0048; Directorate Identifier 2007-NM-
276-AD.

Comments Due Date

    (a) We must receive comments by February 21, 2008.

Affected ADs

    (b) The proposed AD supersedes AD 2006-07-13, Amendment 39-
14540.

Applicability

    (c) This AD applies to AIRBUS Model A310 and A300-600 series 
airplanes, certificated in any category, all certified models, all 
serial numbers, on which rudder Part Number (P/N) A55471500 series 
is fitted, except for those airplanes on which AIRBUS modification 
number 08827 has been incorporated in production.

Subject

    (d) Air Transport Association (ATA) of America Code 55: 
Stabilizers.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Based on some recent in-service findings for fluid ingress and/
or inner skin disbond damage on rudders, AIRBUS decided to introduce 
some further structural inspections to specific rudder areas. This 
type of damage could result in reduced structural integrity of the 
rudder.
    For the reasons stated above, this AD requires the 
accomplishment of a thorough inspection program [a one-time 
inspection and repetitive inspections for damage of the rudder] by 
ultrasonic and/or t[h]ermographic methods, compared to the 
inspections already required by Airworthiness Directive (AD) 2006-
0066, issued on 24 March 2006 [which corresponds to FAA AD 2006-07-
13] as a precautionary measure, in order to verify the structural 
integrity of the rudder.
* * * * *
The corrective actions include reporting both positive and negative 
findings to Airbus, doing a temporary repair, and contacting Airbus 
for repair and doing a permanent repair.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 500 flight cycles or 6 months after the effective 
date of this AD, whichever occurs first, perform a special detailed 
one-time inspection in the areas of rudder hoisting points and 
trailing edge screws, in accordance with the instructions given in 
Airbus Service Bulletin A310-55-2045 or A300-55-6044, both Revision 
01, both dated December 20, 2007, as applicable.
    (i) If no damage is found, within 30 days after the inspection 
or 30 days after the effective date of this AD, whichever occurs 
later, report to Airbus using Appendix 1 or 2, as applicable to the 
airplane configuration, of Airbus Service Bulletin A310-55-2045 or 
A300-55-6044, both Revision 01, as applicable.
    (ii) If any damage is found, within the timescale(s) indicated 
in Airbus Service Bulletin A310-55-2045 or A300-55-6044, both 
Revision 01, as applicable, report to Airbus using Appendix 1 or 2, 
as applicable to the airplane configuration, of Airbus Service 
Bulletin A310-55-2045 or A300-55-6044, both Revision 01, as 
applicable, to get further instructions for repair. Accomplish the 
repair within the timescale(s) indicated in, and in accordance with 
the instructions given in paragraph 3.B.(1)(a) or 3.B.(2)(a), as 
applicable to the airplane configuration, of Airbus Service Bulletin 
A310-55-2045 or A300-55-6044, both Revision 01, as applicable.
    (2) Within 500 flight cycles or 6 months after the effective 
date of this AD, whichever occurs first, perform a special detailed 
inspection along the rudder Z-profile, in accordance with the 
instructions given in Airbus Service Bulletin A310-55-2044 or A300-
55-6043, both Revision 01, both dated December 3, 2007, as 
applicable. For airplanes identified as configuration 01 in the 
service bulletins, repeat the inspection thereafter at intervals not 
to exceed 1,400 flight cycles. For airplanes identified as 
Configuration 02 in the service bulletins, repeat the inspection 
thereafter at intervals not to exceed 5,000 flight cycles. For 
temporary repair along the rudder Z-profile for both airplanes 
identified as configuration 01 and 02, refer to paragraph 3.C.(1) of 
Airbus Service Bulletin A310-55-2044 or A300-55-6043, both Revision 
01, as applicable.
    (i) If no damage is found, within 30 days after the inspection 
or 30 days after the effective date of this AD, whichever occurs 
later, report to AIRBUS using Appendix 1 or 2, as applicable to the 
airplane configuration, of Airbus Service Bulletin A310-55-2044 or 
A300-55-6043, both Revision 01, as applicable.
    (ii) If any damage is found, verify the findings and apply all 
applicable corrective actions within the timescale(s) indicated in, 
and in accordance with instructions given in paragraph 3.B.(1)(a) or 
3.B.(2)(a), as applicable to the airplane configuration, of Airbus 
Service Bulletin A310-55-2044 or A300-55-6043, both Revision 01, as 
applicable. Within 30 days after the inspection or corrective action 
or 30 days after the effective date of this AD, whichever occurs 
later, submit a report to Airbus using Appendix 1 or 2, as 
applicable to the airplane configuration, of Airbus Service Bulletin 
A310-55-2044 or A300-55-6043, both Revision 01, as applicable.

    Note 1: For rudder configuration identification, refer to 
Appendices 3 and 4 of Airbus Service Bulletin A310-55-2044, A310-55-
2045, A300-55-6043, and A300-55-6044, as applicable to the airplane 
model and configuration.

    (3) As of 30 days after the effective date of this AD: No person 
shall install a P/N A55471500 series rudder on any airplane as a 
replacement, unless it has been inspected and repaired, as 
applicable, in accordance with the instructions of Airbus Service 
Bulletins A310-55-2045, Revision 01, dated December 20, 2007, and 
A310-55-2044, Revision 01, dated December 3, 2007; or Airbus Service 
Bulletins A300-55-6044, Revision 01, dated December 20, 2007, and 
A300-55-6043, Revision 01, dated December 3, 2007; as applicable.
    (4) Actions accomplished before the effective date of this AD in 
accordance with Airbus Service Bulletin A300-55-6044 or A310-55-
2045, both dated July 23, 2007, are considered acceptable for 
compliance with the corresponding actions specified in paragraph 
(f)(1) of this AD.
    (5) Actions accomplished before the effective date of this AD in 
accordance with Airbus Service Bulletin A300-55-6043 or A310-55-
2044, both dated July 23, 2007, are considered acceptable for 
compliance with the corresponding actions specified in paragraph 
(f)(2) of this AD.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows: No differences.

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 appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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 2007-0266, dated 
October 8, 2007, and the service bulletins listed in Table 1 of this 
AD, for related information.

[[Page 3659]]



                  Table 1.--Airbus Service Information
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    Airbus Service Bulletin       Revision               Date
------------------------------------------------------------------------
A300-55-6043..................           01  December 3, 2007.
A300-55-6044..................           01  December 20, 2007.
A310-55-2044..................           01  December 3, 2007.
A310-55-2045..................           01  December 20, 2007.
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    Issued in Renton, Washington, on January 15, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
 [FR Doc. E8-977 Filed 1-18-08; 8:45 am]
BILLING CODE 4910-13-P