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CFR Citation: 14 CFR Part 39

Docket ID: [Docket No. FAA-2008-0657; Directorate Identifier 2007-NM-296-AD]

RIN ID: RIN 2120-AA64

NOTICE: PROPOSED RULES

ACTION: Airworthiness Directives:

DOCUMENT ACTION: Notice of proposed rulemaking (NPRM).

SUBJECT CATEGORY: Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes

DATES: We must receive comments on this proposed AD by July 17, 2008.

DOCUMENT SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A300, A310, and A300600 series airplanes. The existing AD currently requires repetitive detailed visual inspections to detect cracks in the pylon thrust and sideload fitting of the wing, and replacement of any cracked pylon thrust and sideload fitting with a new fitting. This proposed AD would
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reduce the threshold and repetitive intervals for the detailed inspection for certain airplanes and would reduce the applicability of the existing AD. This proposed AD results from issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We are proposing this AD to detect and correct cracks in the pylon thrust and sideload fitting of the wing, which could result in reduced structural integrity of the airplane.

SUMMARY: Airbus Model A300, A310, and A300-600 Series Airplanes,

SUPPLEMENTAL INFORMATION

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. FAA20080657; Directorate Identifier 2007NM296AD'' 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 because of 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 July 24, 1998, we issued AD 981611, amendment 3910687 (63 FR 40816, July 31, 1998), for certain Airbus Model A300, A310, and A300 600 series airplanes. That AD requires repetitive detailed visual inspections to detect cracks in the pylon thrust and sideload fitting of the wing, and replacement of any cracked pylon thrust and sideload fitting with a new fitting. That AD resulted from issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We issued that AD to detect and correct cracks in the pylon thrust and sideload fitting of the wing, which could result in reduced structural integrity of the airplane.

Actions Since Existing AD Was Issued

Since we issued AD 981611, Airbus has issued the following service bulletins:
Table.New Service Bulletins
Airbus service bulletin For model
A300570232, Revision 02, A300 series airplanes.
dated February 21, 2000.
A300576079, Revision 04, A300600 series airplanes.
dated February 21, 2000.
A310572075, Revision 03, A310 series airplanes.

dated December 1, 2006.

The repetitive detailed inspections and replacement procedures are essentially identical to those specified in previous issues of the service bulletins. (AD 981611 refers to Airbus Service Bulletins A300570232, Revision 01 (for Model A300 series airplanes); A31057 2075, Revision 01 (for Model A310 series airplanes); and A300576079, Revision 02 (for Model A300600 series airplanes); all dated January 12, 1998; as the appropriate sources of service information for accomplishing the required actions.) Revision 03 of Airbus Service Bulletin A310572075 reduces the detailed inspection thresholds and repeat intervals for certain airplanes. In addition, the effectivity listing of all three service bulletins has been revised to remove airplanes that have been scrapped. No more work is necessary for airplanes on which previous issues of the service bulletins were done.

Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, mandated the service information and issued EASA airworthiness directive 20070243, dated September 4, 2007, to ensure the continued airworthiness of these airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

These airplanes are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. As described in FAA Order 8100.14A, ``Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,'' dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA's findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States.

This proposed AD would supersede AD 981611 and would continue to require, at reduced thresholds and repetitive intervals for certain airplanes, repetitive detailed visual inspections to detect cracks in the pylon thrust and
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sideload fitting of the wing, and would continue to require replacement of any cracked pylon thrust and sideload fitting with a new fitting. This proposed AD would also require accomplishing the actions specified in service information described previously.

Differences Between Proposed Rule and EASA AD

The proposed AD would differ from the parallel EASA airworthiness directive in that it would not allow for adjustment in compliance time based on airplane utilization. In developing an appropriate compliance time for this proposed AD, the FAA considered not only the manufacturer's recommendation, but the degree of urgency associated with addressing the subject unsafe condition, and the average utilization of the affected fleet. In light of these factors, we find the compliance times specified in paragraphs (f)(1) and (f)(2) of this proposed AD to be warranted, in that they represent an appropriate interval of time allowable for affected airplanes to continue to operate without compromising safety.

Change to Existing AD

This proposed AD would retain all requirements of AD 981611. Since AD 981611 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table:
Revised Paragraph Identifiers
Corresponding requirement Requirement in AD 981611 in this proposed AD paragraph (a)............................. paragraph (f).

paragraph (b)............................. paragraph (g).

In addition, we have revised the applicability of this proposed AD to refer to the latest revisions of the service information described previously.

We also changed all references to a ``detailed visual inspection'' in the existing AD to ``detailed inspection'' in this action. Costs of Compliance

This proposed AD would affect about 164 Model A300, A310, and A300 600 series airplanes of U.S. registry.

The inspections that are required by AD 981611 and retained in this proposed AD take about 3 work hours per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the currently required actions is $39,360, or $240 per airplane, per inspection cycle.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that the proposed regulation:

1. Is not a ``significant regulatory action'' under Executive Order 12866;

2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39AIRWORTHINESS DIRECTIVES

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

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

Sec. 39.13 [Amended]

2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by removing amendment 3910687 (63 FR 40816, July 31, 1998) and adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA20080657; Directorate Identifier 2007NM 296AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by July 17, 2008.
Affected ADs
(b) This AD supersedes AD 981611.
Applicability
(c) This AD applies to Airbus airplanes identified in Table 1 of this AD, certificated in any category.
Table 1.Applicability
As identified in Airbus service Model bulletin
(1) A300 series airplanes............ A300570232, Revision 02, dated February 21, 2000.
(2) A310 series airplanes............ A310572075, Revision 03, dated December 1, 2006.
(3) A300600 series airplanes........ A300576079, Revision 04, dated February 21, 2000.
Unsafe Condition
(d) This AD results from issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We are issuing this AD to detect and correct cracks in the pylon thrust and sideload fitting of the wing, which could result in reduced structural integrity of the airplane.
Compliance
(e) You are responsible for having the actions required by this AD performed within
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the compliance times specified, unless the actions have already been done.
Requirements of AD 981611:
Repetitive Detailed Inspections at Reduced Thresholds and Repeat Intervals for Certain Airplanes
(f) At the applicable time specified in paragraph (f)(1) or (f)(2) of this AD: Perform a detailed inspection to detect cracks in the pylon thrust and sideload fitting of the wing, in accordance with Airbus Service Bulletin A300570232, Revision 01 (for Model A300 series airplanes); A310572075, Revision 01 (for Model A310 series airplanes); or A300576079, Revision 02 (for Model A300600 series airplanes); all dated January 12, 1998; as applicable; except as provided by paragraph (h) of this AD.
(1) For Model A300 and A300600 series airplanes: Inspect prior to the accumulation of 2,800 total flight cycles, or within 18 months after September 4, 1998 (the effective date AD 981611), whichever occurs later, and thereafter at intervals not to exceed 2,800 flight cycles.
(2) For Model A310 series airplanes: Inspect at the earlier of the times specified in paragraph (f)(2)(i) and (f)(2)(ii) of this AD. Repeat thereafter at the applicable intervals specified in Table 3 of this AD.
(i) Prior to the accumulation of 2,800 total flight cycles, or within 18 months after September 4, 1998, whichever occurs later. (ii) At the applicable time specified in Table 2 of this AD. Table 2.Reduced Inspection Thresholds for Model A310 Series Airplanes Compliance time (whichever occurs later) Model
Threshold Grace period A310200 series airplanes... Before the Within 800 flight accumulation of cycles or 1,600 1,500 total flight flight hours after cycles or 3,000 the effective date total flight hours of this AD, since first flight, whichever occurs whichever occurs first. first.
A310300 series airplanes Before the Within 800 flight (short range). accumulation of cycles or 1,600 1,300 total flight flight hours after cycles or 3,800 the effective date total flight hours of this AD, since first flight, whichever occurs whichever occurs first. first.
A310300 series airplanes Before the Within 800 flight (long range). accumulation of 800 cycles or 1,600 total flight cycles flight hours after or 4,000 total the effective date flight hours since of this AD, first flight, whichever occurs whichever occurs first. first.
Table 3.Reduced Repeat Intervals for Model A310 Series Airplanes Repeat the detailed And, thereafter For Model inspection at the at intervals not later of to exceed A310200 series airplanes..... Within 1,500 flight 1,500 flight cycles or 3,000 cycles or 3,000 flight hours since flight hours, the last detailed whichever inspection, whichever occurs first. occurs first; or
within 800 flight
cycles or 1,600
flight hours after
the effective date of
this AD, whichever
occurs first.
A310300 series airplanes Within 1,300 flight 1,300 flight (short range). cycles or 3,800 cycles or 3,800 flight hours since flight hours, the last detailed whichever inspection, whichever occurs first. occurs first; or
within 800 flight
cycles or 1,600
flight hours after
the effective date of
this AD, whichever
occurs first.
A310300 series airplanes Within 800 flight 800 flight (long range). cycles or 4,000 cycles or 4,000 flight hours since flight hours, the last detailed whichever inspection, whichever occurs first. occurs first; or
within 800 flight
cycles or 1,600
flight hours after
the effective date of
this AD, whichever
occurs first.
Corrective Action
(g) If any crack is detected during any inspection required by paragraph (f) of this AD, prior to further flight, replace the pylon thrust and sideload fitting with a new fitting in accordance with Airbus Service Bulletin A300570232, Revision 01 (for Model A300 series airplanes); A310572075, Revision 01 (for Model A310 series airplanes); or A300576079, Revision 02 (for Model A300600 series airplanes); all dated January 12, 1998; as applicable; except as provided by paragraph (h) of this AD.
New Actions Required by This AD:
New Service Information
(h) For all airplanes: As of the effective date of this AD, use only the Accomplishment Instructions of the applicable service bulletin specified in Table 4 of this AD to do the repetitive detailed inspections required by paragraph (f) of this AD and the replacement required by paragraph (g) of this AD.
Table 4.New Service Bulletins
Airbus service bulletin For model
(1) A300570232, Revision A300 series airplanes.
02, dated February 21, 2000.
(2) A300576079, Revision A300600 series airplanes.
04, dated February 21, 2000.
(3) A310572075, Revision A310 series airplanes.
03, dated December 1, 2006.
(i) Actions done before the effective date of this AD in accordance with Airbus Service Bulletins A300576079, Revision 02, dated January 12, 1998, or Revision 03, dated October 25, 1999 (for Model A300600 series airplanes); A310572075, Revision 01, dated January 12, 1998, or Revision 02, dated February 21, 2000 (for Model A310 series airplanes); or A300570232, Revision 01, dated January 12, 1998 (for Model A300 series airplanes); are acceptable for compliance with the corresponding requirements of this AD.
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Alternative Methods of Compliance (AMOCs)
(j) The Manager, International Branch, ANM116, 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 980573356; telephone (425) 2271138; fax (425) 2271149. 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.
Related Information
(k) European Aviation Safety Agency (EASA) airworthiness directive 20070243, dated September 4, 2007, also addresses the subject of this AD.

Issued in Renton, Washington, on June 10, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E813566 Filed 61608; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 980573356; telephone (425) 2271138; fax (425) 2271149.