Document ID: FAA-2008-0908-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Model A310 Series Airplanes
Posted Date: 2008-08-26T04:00Z

[Federal Register: August 26, 2008 (Volume 73, Number 166)]
[
Proposed Rules]               
[Page 50250-50253]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26au08-16]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0908; Directorate Identifier 2007-NM-190-AD]

RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 

Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 

directive (AD) that applies to all Airbus Model A310 series airplanes. 

The existing AD currently requires repetitive detailed inspections to 

detect cracks propagating from the fastener holes that attach the left- 

and right-hand pick-up angles at frame 40 to the wing lower skin and 

fuselage panel, and corrective actions, if necessary. This proposed AD 

would revise the intervals for accomplishing the repetitive detailed 

inspections and would provide for an optional terminating modification 

for the repetitive inspections. This proposed AD results from mandatory 

continuing airworthiness information originated by an aviation 

authority of another country to identify and correct an unsafe 

condition on an aviation product. We are proposing this AD to prevent 

reduced structural integrity of the airplane due to fatigue damage and 

consequent cracking of the pick-up angles at frame 40.

DATES: We must receive comments on this proposed AD by September 25, 

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 W12-140, 1200 New 

Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal holidays.

    For service information identified in this AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://

www.regulations.gov; or in person at the Docket Management Facility 

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 Office (telephone 800-647-5527) is in the 

ADDRESSES section. Comments will be

[[Page 50251]]

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-2008-0908; 

Directorate Identifier 2007-NM-190-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 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 December 22, 2000, we issued AD 2000-26-14, amendment 39-12064 

(66 FR 1031, January 5, 2001), for all Airbus Model A310 series 

airplanes. That AD requires repetitive detailed visual inspections to 

detect cracks propagating from the fastener holes that attach the left- 

and right-hand pick-up angles at frame 40 to the wing lower skin and 

fuselage panel, and corrective actions, if necessary. That AD resulted 

from a report indicating that structural damage was found on the pick-

up angles at the junction between the wing lower surface and the 

fuselage skin at frame 40. We issued that AD to prevent reduced 

structural integrity of the airplane due to fatigue damage and 

consequent cracking of the pick-up angles at frame 40.

Actions Since Existing AD Was Issued

    Since we issued AD 2000-26-14, European Aviation Safety Agency 

(EASA), which is the Technical Agent for the Member States of the 

European Community, has informed us that, as a result of A310 extended 

service goal activities, the thresholds and repetitive intervals for 

the existing repetitive detailed visual inspections required by AD 

2000-26-14 must be modified to adequately address the identified unsafe 

condition.

Relevant Service Information

    Airbus has issued Revision 03 of Service Bulletin A310-53-2111, 

dated May 21, 2007 (AD 2000-26-14 refers to Airbus Service Bulletin 

A310-53-2111, Revision 01, dated June 21, 2000, as the appropriate 

source of service information for accomplishing the required actions). 

The inspection procedures specified in Revision 03 are essentially 

identical to those specified in Revision 01. Revision 03 revises the 

thresholds and repetitive intervals for the inspections and thresholds 

for replacing pick-up angles. No additional work is required by 

Revision 03 for airplanes inspected in accordance with earlier 

revisions. Accomplishing the actions specified in the service 

information is intended to adequately address the unsafe condition. The 

EASA mandated Service Bulletin A310-53-2111, Revision 03, and issued 

airworthiness directive 2007-0184, dated July 3, 2007, to ensure the 

continued airworthiness of these airplanes in the European Union.

    Airbus also issued Service Bulletin A310-53-2119, Revision 01, 

dated February 27, 2007. The service bulletin describes procedures for 

removing the existing pick-up angles and installing a reinforced 

doubler between frames (FR) FR40 and FR41, and doing applicable related 

investigative and corrective actions. The related investigative actions 

include inspecting the diameters of the holes, and doing a rotating 

probe inspection of the holes 1 through 70. The corrective actions 

involve contacting the airplane manufacturer for repair procedures. 

EASA airworthiness directive 2007-0184 refers to this service bulletin 

as an optional terminating action for the repetitive inspections 

specified in Service Bulletin A310-53-2111, Revision 03.

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 2000-26-14 and would continue 

to require repetitive detailed inspections to detect cracks propagating 

from the fasteners holes that attach the left- and right-hand pick-up 

angles at frame 40 to the wing lower skin and fuselage panel, and 

corrective actions, if necessary. This proposed AD would revise the 

intervals for accomplishing the repetitive detailed inspections and 

would provide for an optional terminating modification for the 

repetitive inspections.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2000-26-14. 

Since AD 2000-26-14 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 in

      Requirement in AD 2000-26-14               this proposed AD

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

paragraph (a)...........................  paragraph (f).

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

paragraph (c)...........................  paragraph (h).

paragraph (d)...........................  paragraph (i).

paragraph (e)...........................  paragraph (j).

paragraph (f)...........................  paragraph (k).

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

    We also have 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 68 Model A310 series airplanes 

of U.S. registry.

    The inspections that are required by AD 2000-26-14 and retained in 

this proposed AD take about 2 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 $10,880, or $160 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.

[[Page 50252]]

    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 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 

removing amendment 39-12064 (66 FR 1031, January 5, 2001) and adding 

the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2008-0908; Directorate Identifier 2007-NM-

190-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by September 

25, 2008.

Affected ADs

    (b) This AD supersedes AD 2000-26-14.

Applicability

    (c) This AD applies to Airbus Model A310 series airplanes, 

certificated in any category, except those airplanes modified in-

service in accordance with Airbus Service Bulletin A310-53-2119, 

dated October 25, 2005; or Revision 01, dated February 27, 2007.

Unsafe Condition

    (d) This AD results from mandatory continuing airworthiness 

information originated by an aviation authority of another country 

to identify and correct an unsafe condition on an aviation product. 

We are issuing this AD to prevent reduced structural integrity of 

the airplane due to fatigue damage and consequent cracking of the 

pick-up angles at frame 40.

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 2000-26-14

Inspections and Corrective Actions

    (f) Perform a detailed inspection to detect cracks propagating 

from the fastener holes that attach the left- and right-hand pick-up 

angles at frame 40 to the wing lower skin and fuselage panel, at the 

time specified in paragraph (g), (h), (i), (j) or (k) of this AD, as 

applicable. Perform the actions in accordance with Figure 2, Sheet 

1, ``Synoptic Chart,'' of Airbus Service Bulletin A310-53A2111, 

Revision 01, dated June 21, 2000, except as provided by paragraph 

(l) of this AD.

    (1) If no cracking is found during the inspection required by 

paragraph (f) of this AD, repeat the detailed inspection thereafter 

at the interval specified in paragraph (f)(1)(i) or (f)(1)(ii) of 

this AD, as applicable, except as provided by paragraph (n) of this 

AD.

    (i) For Model A310-200 series airplanes: Except as provided by 

paragraph (i) of this AD, repeat the inspection thereafter at 

intervals not to exceed 1,000 flight cycles or 2,600 flight hours, 

whichever occurs first.

    (ii) For Model A310-300 series airplanes: Except as provided by 

paragraphs (i) of this AD, repeat the inspection thereafter at 

intervals not to exceed 850 flight cycles or 2,800 flight hours, 

whichever occurs first.

    (2) If any cracking is found during the inspection required by 

paragraph (f) of this AD, prior to further flight, perform 

applicable corrective actions (including repair (drilling and 

reaming a crack stop hole in the pick-up angle, performing a 

Rototest inspection and repetitive detailed inspections at the time 

specified in the service bulletin, and replacing the pick-up angle 

with a new angle at the time specified in the service bulletin, 

except as provided by paragraph (o) of this AD); or immediate 

replacement of any cracked angle with a new angle). Perform the 

actions and repetitive inspections in accordance with Figure 2, 

Sheet 1, ``Synoptic Chart,'' of Airbus Service Bulletin A310-

53A2111, Revision 01, dated June 21, 2000, except as provided by 

paragraph (l) of this AD.

    Note 1: Accomplishment of the actions required by paragraph (f) 

of this AD in accordance with Airbus Service Bulletin A310-53A2111, 

dated April 21, 2000, is considered to be acceptable for compliance 

with the requirements of that paragraph.

Compliance Times

    (g) For Model A310-200 series airplanes: Except as provided by 

paragraphs (i), (j), and (k) of this AD, perform the initial 

inspection at the later of the times specified in paragraphs (g)(1) 

and (g)(2) of this AD.

    (1) Prior to the accumulation of 7,900 total flight cycles or 

23,600 total flight hours, whichever occurs first.

    (2) Within 700 flight cycles or 1,200 flight hours after 

February 9, 2001 (the effective date of AD 2000-26-14), whichever 

occurs first.

    (h) For Model A310-300 series airplanes: Except as provided by 

paragraphs (i), (j), and (k) of this AD, perform the initial 

inspection required by paragraph (f) of this AD at the later of the 

times specified in paragraphs (h)(1) and (h)(2) of this AD.

    (1) Prior to the accumulation of 6,700 total flight cycles or 

24,700 total flight hours, whichever occurs first.

    (2) Within 700 flight cycles or 1,200 flight hours after 

February 9, 2001, whichever occurs first.

    (i) For airplanes that have accumulated more than 18,000 total 

flight cycles or 53,000 total flight hours as of February 9, 2001: 

Perform the initial inspection required by paragraph (f) of this AD 

within 350 flight cycles or 600 flight hours after February 9, 2001, 

whichever occurs first. Repeat the inspection thereafter at 

intervals not to exceed 350 flight cycles or 600 flight hours, 

whichever occurs first.

    (j) For airplanes having manufacturer's serial number 0162 

through 0326 inclusive, on which Airbus Service Bulletin A310-53-

2014 has been accomplished prior to February 9, 2001: The initial 

inspection threshold may be counted from the date of accomplishment 

of Airbus Service Bulletin A310-53-2014.

    (k) For airplanes on which a pick-up angle has been replaced: 

For that pick-up angle only, the initial inspection threshold may be 

counted from the date of installation of the new pick-up angle.

    Note 2: For the purposes of this AD, a detailed inspection is 

defined as: ``An intensive visual examination of a specific 

structural area, system, installation, or assembly to detect damage, 

failure, or irregularity. Available lighting is normally 

supplemented with a direct source of good lighting at intensity 

deemed appropriate by the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface cleaning and elaborate 

access procedures may be required.''

[[Page 50253]]

New Requirements of This AD

New Revisions of Service Bulletin

    (l) As of the effective date of this AD, use only the 

Accomplishment Instructions of Airbus Service Bulletin A310-53-2111, 

Revision 03, dated May 21, 2007, to do the inspections and 

corrective actions required by paragraph (f) of this AD; except 

where Figure 2 Sheet 2 of the service bulletin specifies actions for 

crack length of ``<54 mm (2.126 in.)'' and ``<69 mm (2.716 in.),'' 

this AD requires the corresponding actions for crack lengths less 

than or equal to those measurements.

    (m) Inspections and applicable corrective actions done before 

the effective date of this AD in accordance with Airbus Service 

Bulletin A310-53-2111, Revision 02, dated October 25, 2005, are 

acceptable for compliance with the requirements of paragraph (f) of 

this AD.

Revised Repetitive Intervals for Detailed Inspections

    (n) As of the effective date of this AD, repeat the detailed 

inspections for no crack findings required by paragraph (f)(1)(i), 

(f)(1)(ii), or (i) of this AD, as applicable, at the applicable 

times specified in Table 1 of this AD, until the modification 

specified in paragraph (p) of this AD is done.

                     Table 1--Revised Repetitive Intervals for Certain Detailed Inspections

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                                     Repeat the inspection at    Repeat the inspection at     And thereafter at

            For model--             the later of the following  the later of the following    intervals not to

                                              times--                     times--                 exceed--

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(1) A310-200 series airplanes.....  Within 950 flight cycles    Within 50 flight cycles or  950 flight cycles or

                                     or 1,900 flight hours       250 flight hours after      1,900 flight hours,

                                     since the last inspection   the effective date of       whichever occurs

                                     required by paragraph       this AD, whichever occurs   first.

                                     (f)(1)(ii) or (i) of this   first.

                                     AD, whichever occurs

                                     first.

(2) A310-300 series airplanes       Within 900 flight cycles    Within 50 flight cycles or  900 flight cycles or

 (short range).                      or 2,550 flight hours       250 flight hours after      2,550 flight hours,

                                     since the last inspection   the effective date of       whichever occurs

                                     required by paragraph       this AD, whichever occurs   first.

                                     (f)(1)(ii) or (i) of this   first.

                                     AD, whichever occurs

                                     first.

(3) A310-300 series airplanes       Within 800 flight cycles    Within 50 flight cycles or  800 flight cycles or

 (long range).                       or 4,000 flight hours       250 flight hours after      4,000 flight hours,

                                     since the last inspection   the effective date of       whichever occurs

                                     required by paragraph       this AD, whichever occurs   first.

                                     (f)(1)(ii) or (i) of this   first.

                                     AD, whichever occurs

                                     first.

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Revised Threshold for Replacing the Pick-Up Angles

    (o) As of the effective date of this AD, do the replacement of 

the pick-up angle required by paragraph (f)(2) of this AD, at the 

applicable time specified in Table 2 of this AD.

                            Table 2--Revised Thresholds for Replacing Pick-Up Angles

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

 

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For model--                             Replace at the earlier of the following times--

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(1) A310-200 series airplanes.........  At the time specified in        Within 1,500 flight cycles or 3,000

                                         paragraph (f)(2) of this AD     flight hours since the last detailed

                                         for replacing the pick-up       inspection, or within 30 days after the

                                         angle.                          effective date of this AD, whichever

                                                                         occurs later.

(2) A310-300 series airplanes (short    At the time specified in        Within 1,600 flight cycles or 4,600

 range).                                 paragraph (f)(2) of this AD     flight hours since the last detailed

                                         for replacing the pick-up       inspection, or within 30 days after the

                                         angle.                          effective date of this AD, whichever

                                                                         occurs later.

(3) A310-300 series airplanes (long     At the time specified in        Within 1,400 flight cycles or 7,200

 range).                                 paragraph (f)(2) of this AD     flight hours since the last detailed

                                         for replacing the pick-up       inspection, or within 30 days after the

                                         angle.                          effective date of this AD, whichever

                                                                         occurs later.

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Optional Terminating Modification

    (p) Remove the existing pick-up angles and install a reinforced 

doubler between frames (FR) FR40 and FR41, and perform applicable 

related investigative and corrective actions by accomplishing all 

the applicable actions specified in the Accomplishment Instructions 

of Airbus Service Bulletin A310-53-2119, Revision 01, dated February 

27, 2007; except as provided by paragraph (q) of this AD. 

Accomplishing these actions ends the repetitive inspections required 

by this AD.

    (q) If any crack is detected and Airbus Service Bulletin A310-

53-2119, Revision 01, dated February 27, 2007, specifies to contact 

Airbus: Before further flight, repair the crack using a method 

approved by either the Manager, International Branch, ANM-116, 

Transport Airplane Directorate, FAA; or the European Aviation Safety 

Agency (EASA) (or its delegated agent).

    (r) Actions done before the effective date of this AD in 

accordance with the Accomplishment Instructions of Airbus Service 

Bulletin A310-53-2119, dated October 25, 2005, are acceptable for 

compliance with the corresponding requirements of paragraph (p) of 

this AD.

Alternative Methods of Compliance (AMOCs)

    (s) The Manager, International Branch, ANM-116, 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: 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. 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

    (t) EASA airworthiness directive 2007-0184, dated July 3, 2007, 

also addresses the subject of this AD.

    Issued in Renton, Washington, on August 18, 2008.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification 

Service.

[FR Doc. E8-19715 Filed 8-25-08; 8:45 am]

BILLING CODE 4910-13-P