FR Doc E8-19715

[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).

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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

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Corresponding requirement in

Requirement in AD 2000-26-14 this proposed AD

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

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

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

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

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

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

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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

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