50250 Federal Register / Vol. 73, No. 166 / Tuesday, August 26, 2008 / Proposed Rules 

Model Avro 146–RJ70A, 146–RJ85A, and 

146–RJ100A airplanes, certificated in any 

category. 

Unsafe Condition 

(d) This AD results from issuance of a later 

revision to the airworthiness limitations of 

the BAe/Avro 146 Aircraft Maintenance 

Manual (AMM), which specifies new 

inspections and compliance times for 

inspection and replacement actions. We are 

issuing this AD to ensure that fatigue 

cracking of certain structural elements is 

detected and corrected; such fatigue cracking 

could adversely affect the structural integrity 

of these airplanes. 

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. 

Certain Requirements of AD 2005–23–12 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance (AMOC) 

according to paragraph (i) of this AD. The 

request should include a description of 

changes to the required inspections that will 

ensure the continued operational safety of 

the airplane. 

Airworthiness Limitations Revision 

(f) Within 30 days after December 27, 2005 

(the effective date of AD 2005–23–12), revise 

the Airworthiness Limitations Section (ALS) 

of the Instructions for Continued 

Airworthiness to incorporate new and more 

restrictive life limits for certain items and 

new and more restrictive inspections to 

detect fatigue cracking in certain structures, 

in accordance with a method approved by 

the Manager, International Branch, ANM–

116, Transport Airplane Directorate, FAA; or 

the Civil Aviation Authority (or its delegated 

agent). Section 05–10–01, dated July 15, 

2005, of Chapter 5 of the BAe/Avro 146 

Aircraft Maintenance Manual is one 

approved method. This section references 

other sections of the AMM. The applicable 

revision level of the referenced sections is the 

revision level that is in effect on December 

27, 2005. 

New Requirements of This AD 

Later Revision for Airworthiness Limitations 

(g) Within 30 days after the effective date 

of this AD, revise the ALS of the Instructions 

for Continued Airworthiness to incorporate 

new and more restrictive life limits for 

certain items and new and more restrictive 

inspections to detect fatigue cracking in 

certain structures, in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (or its delegated 

agent). Sections 05–10 and 05–20, both dated 

August 15, 2007, of Chapter 5 of the BAe/ 

Avro 146 Aircraft Maintenance Manual is 

one approved method. Those sections 

reference other sections of the AMM. The 

applicable revision level of the referenced 

sections is the revision level that is in effect 

on the effective date of this AD. Incorporating 

the new and more restrictive life limits and 

inspections into the ALS terminates the 

requirements of paragraphs (f) and (g) of this 

AD, and after incorporation has been done, 

the limitations required by paragraph (f) of 

this AD may be removed from the ALS. 

(h) Except as specified in paragraph (i) of 

this AD: After the actions specified in 

paragraph (f) or (g) of this AD have been 

accomplished, no alternative inspections or 

inspection intervals may be approved for the 

structural elements specified in the 

documents listed in paragraph (f) or (g) of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i) 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: Todd Thompson, Aerospace 

Engineer, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–4056; telephone (425) 227–1175; 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 

(j) The European Aviation Safety Agency 

airworthiness directive 2007–0271, dated 

October 16, 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. E8–19714 Filed 8–25–08; 8:45 am] 

BILLING CODE 4910–13–P 

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 


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Federal Register / Vol. 73, No. 166 / Tuesday, August 26, 2008 / Proposed Rules 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

Requirement in AD 

2000–26–14 

Corresponding 

requirement in 

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. 


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50252 Federal Register / Vol. 73, No. 166 / Tuesday, August 26, 2008 / Proposed Rules 

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. 

§ 39.13 [Amended] 

2. The Federal Aviation 

Administration (FAA) amends § 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 pickup 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 pickup 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.’’


sroberts on PROD1PC76 with PROPOSALS
Federal Register / Vol. 73, No. 166 / Tuesday, August 26, 2008 / Proposed Rules 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

For model— Repeat the inspection at the later of the 

following times—

Repeat the inspection at the later of the 

following times—

And thereafter at intervals not 

to exceed—

(1) A310–200 series 

airplanes.

Within 950 flight cycles or 1,900 flight 

hours since the last inspection required 

by paragraph (f)(1)(ii) or (i) of this AD, 

whichever occurs first.

Within 50 flight cycles or 250 flight hours 

after the effective date of this AD, 

whichever occurs first.

950 flight cycles or 1,900 flight 

hours, whichever occurs first. 

(2) A310–300 series 

airplanes (short 

range).

Within 900 flight cycles or 2,550 flight 

hours since the last inspection required 

by paragraph (f)(1)(ii) or (i) of this AD, 

whichever occurs first.

Within 50 flight cycles or 250 flight hours 

after the effective date of this AD, 

whichever occurs first.

900 flight cycles or 2,550 flight 

hours, whichever occurs first. 

(3) A310–300 series 

airplanes (long 

range).

Within 800 flight cycles or 4,000 flight 

hours since the last inspection required 

by paragraph (f)(1)(ii) or (i) of this AD, 

whichever occurs first.

Within 50 flight cycles or 250 flight hours 

after the effective date of this AD, 

whichever occurs first.

800 flight cycles or 4,000 flight 

hours, whichever occurs first. 

Revised Threshold for Replacing the PickUp 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

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

(1) A310–200 series airplanes.At the time specified in paragraph (f)(2) of this 

AD for replacing the pick-up angle.

Within 1,500 flight cycles or 3,000 flight hours since the last detailed 

inspection, or within 30 days after the effective date of this AD, 

whichever occurs later. 

(2) A310–300 series airplanes (short range).At the time specified in paragraph (f)(2) of this 

AD for replacing the pick-up angle.

Within 1,600 flight cycles or 4,600 flight hours since the last detailed 

inspection, or within 30 days after the effective date of this AD, 

whichever occurs later. 

(3) A310–300 series airplanes (long range).At the time specified in paragraph (f)(2) of this 

AD for replacing the pick-up angle.

Within 1,400 flight cycles or 7,200 flight hours since the last detailed 

inspection, or within 30 days after the effective date of this AD, 

whichever occurs later. 

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 


sroberts on PROD1PC76 with PROPOSALS