56262 Federal Register / Vol. 72, No. 191 / Wednesday, October 3, 2007 / Rules and Regulations 

(2) On August 29, 2006 (71 FR 42026, July 

25, 2006), the Director of the Federal Register 

approved the incorporation by reference of 

the service bulletins listed in Table 4 of this 

AD. 

TABLE 4.—MATERIAL PREVIOUSLY

INCORPORATED BY REFERENCE

Airbus Service 

Bulletin— Dated—

A300–28–0079 ......... September 29, 2005. 

A300–28–0081 ......... July 20, 2005. 

A310–28–2142 ......... August 26, 2005. 

A310–28–2143 ......... July 20, 2005. 

A310–28–2153 ......... July 20, 2005. 

(3) Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on 

September 21, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–19206 Filed 10–2–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27015; Directorate 

Identifier 2006–NM–169–AD; Amendment 

39–15215; AD 2007–20–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–111 and A318–112 Airplanes and 

Model A319, A320, and A321 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding two 

existing airworthiness directives (ADs). 

One AD applies to all Airbus Model 

A319 and A320 airplanes and currently 

requires repetitive ultrasonic 

inspections to detect fatigue cracking in 

the wing/fuselage joint cruciform 

fittings, and corrective actions if 

necessary. The other AD applies to all 

Airbus Model A319, A320, and A321 

airplanes and currently requires a 

revision to the Airworthiness 

Limitations section (ALS) of the 

Instructions for Continued 

Airworthiness (ICA). This new AD 

requires new revisions to the ALS of the 

ICA to incorporate service life limits for 

certain items and inspections to detect 

fatigue cracking, accidental damage, or 

corrosion in certain structures; and 

accomplishment of the repetitive 

ultrasonic inspections of the wing/ 

fuselage joint cruciform fittings in 

accordance with the revised ALS of the 

ICA. This AD also adds airplanes to the 

applicability. This AD results from 

issuance of new and more restrictive 

service life limits and structural 

inspections based on fatigue testing and 

in-service findings. We are issuing this 

AD to detect and correct fatigue 

cracking, accidental damage, or 

corrosion in principal structural 

elements and to prevent failure of 

certain life limited parts, which could 

result in reduced structural integrity of 

the airplane. 

DATES: This AD becomes effective 

November 7, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 7, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2141; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Operations office (telephone (800) 647–

5527) is located on the ground floor of 

the West Building at the DOT street 

address stated in the ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2004–03–06, amendment 

39–13450 (69 FR 5909, February 9, 

2004) and AD 2005–02–09, amendment 

39–13954 (70 FR 3871, January 27, 

2005). AD 2004–03–06 applies to all 

Airbus Model A319 and A320 airplanes, 

and AD 2005–02–09 applies to all 

Airbus Model A319, A320, and A321 

airplanes. That NPRM was published in 

the Federal Register on January 26, 

2007 (72 FR 3768). That NPRM 

proposed to require new revisions to the 

Airworthiness Limitations section (ALS) 

of the Instructions for Continued 

Airworthiness (ICA) to incorporate 

service life limits for certain items and 

inspections to detect fatigue cracking, 

accidental damage, or corrosion in 

certain structures; and accomplishment 

of the repetitive ultrasonic inspections 

of the wing/fuselage joint cruciform 

fittings in accordance with the revised 

ALS of the ICA. That NPRM also 

proposed to add airplanes to the 

applicability. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Support for the NPRM 

Airbus supports the NPRM. 

Northwest Airlines and United Airlines 

agree with the intent of the NPRM. 

Request To Incorporate Certain Service 

Information 

The Air Transport Association (ATA), 

on behalf of its member U.S. Airways, 

requests that we incorporate the 

following documents into this AD: 

Airbus Operator Information Telex 

(OIT) 999.0049/06, dated April 14, 2006; 

Airbus OIT 999.0055/06/CL, dated May 

4, 2006; and the Airbus A318/A319/ 

A320/A321 Scheduled Maintenance 

Data (SMD). The commenters further 

request that we revise this AD to allow 

operators to use later revisions of Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE–M4/ 

95A.0252/96 (hereafter referred to as the 

‘‘Airbus ALI’’), as acceptable for 

compliance with the requirements of 

this AD. As justification for its request, 

US Airways states that Airbus will be 

revising the SMD and ALI on a regular 

basis. 

We agree to refer to Airbus ALI, Issue 

08, dated March 2006 (approved by the 

European Aviation Safety Agency 

(EASA) on January 4, 2007); and Issue 

09, dated November 2006 (approved by 

the EASA on May 21, 2007); as 

appropriate sources of service 

information for accomplishing the 

actions required by paragraph (i) of this 

AD. We have also revised paragraph (j) 


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of this AD accordingly. In the NPRM, 

we referred to Airbus ALI, Issue 7, dated 

December 2005 (approved by the EASA 

on February 7, 2006), as the appropriate 

source of service information. Issue 08 

of the Airbus ALI adds Model A320–215 

and –216 airplanes and Model A321–

214 airplanes to the applicability of 

certain ALI tasks. Since these airplanes 

have not yet been type certificated in 

the U.S., incorporating Issue 08 of the 

Airbus ALI into this AD does not 

expand the scope of the AD. Issue 09 of 

the Airbus ALI extends the compliance 

time for certain ALI tasks and adds new 

tasks for Model A318–121 and –122 

airplanes. This AD does not apply to 

Model A318–121 and –122 airplanes, 

since Issue 09 of the Airbus ALI was 

approved as part of the type certification 

basis for the Model A318–121 and –122 

airplanes. Therefore, incorporating Issue 

09 of the Airbus ALI into this AD does 

not expand the scope of the AD. 

We do not agree to allow the use of 

future revisions to the Airbus ALI 

because we are prohibited from referring 

to documents that do not yet exist. 

Additionally, we do not agree to refer to 

the other service information requested 

by the commenters, since this AD only 

mandates incorporation of Issue 7, 08, 

or 09 of the Airbus ALI and Sub-parts 

1–2 and 1–3 of Airbus A318/A319/ 

A320/A321 ALS Part 1—Safe Life 

Airworthiness Limitation Items, dated 

February 28, 2006. 

Request To Extend Grace Period 

United Airlines requests that, if ALI 

Tasks 552007–01–1 and 552007–01–2 

are required, we add an additional grace 

period for accomplishing these tasks. As 

justification, United Airlines states that 

a longer grace period is needed to 

account for the development of new 

tooling or a non-destructive inspection 

method that could produce more 

conclusive findings than the current 

inspection method. United Airlines 

states that it has discussed this subject 

with Airbus, and that Airbus and the 

EASA are reviewing the matter. United 

Airlines further states that Airbus has 

not provided allowable damage limits in 

Chapter 55–21–11, page series 101, of 

the Airbus Structural Repair Manual 

(SRM) for acceptable findings, which 

would permit proceeding without repair 

until the next inspection. United 

Airlines believes that Airbus is pursuing 

such relief; however, the timing is 

unknown. 

We agree to extend the grace period 

for accomplishing ALI Task 552007–01–

1 from 20 months to 40 months, in 

accordance with Issue 09 of the Airbus 

ALI. As discussed previously, we have 

revised paragraphs (i) and (j) of this AD 

to refer to Issue 09 of the Airbus ALI. 

However, we do not agree to extend the 

grace period for ALI Task 552007–01–2. 

The commenter has not recommended a 

specific amount of time for extending 

the compliance time, or provided data 

showing that an extension in the 

compliance time would provide an 

acceptable level of safety. If data are 

submitted to substantiate that such an 

adjustment would provide an acceptable 

level of safety, under the provisions of 

paragraph (l) of this AD, we might 

approve the request for an adjustment to 

the compliance time. Further, if the 

EASA issues a new airworthiness 

directive to extend the compliance time 

for these tasks or to revise the task 

instructions, we will consider further 

rulemaking. We have not revised this 

AD in this regard. 

Request To Exclude Certain ALI Tasks 

The ATA, on behalf of its member 

United Airlines, and Northwest Airlines 

(NWA) request that we exclude ALI 

Tasks 552007–01–1 and 552007–01–2 

from the requirements of this AD. These 

ALI tasks involve thermographic 

inspections to detect the presence of 

water in the carbon fiber composite 

structure of the elevator control 

surfaces. United Airlines states that, 

based on inspections it has conducted, 

this method of inspection has not 

provided conclusive evidence of water 

ingression; its findings were limited to 

manufacturing defects. United Airlines 

also states that the inspection process is 

questionable, and that there is no 

effective non-destructive verification 

tool currently available to validate the 

presence of water. United Airlines 

asserts that the current process is more 

destructive to the elevator, as the skins 

and core in the area were removed and 

subsequently repaired. 

United Airlines also states that these 

ALI tasks were incorporated into the 

Airbus ALI without MSG–3 Analysis 

review by the Industry Structures 

Working Group. United Airlines states 

that composite structures are not subject 

to fatigue-based analysis and, therefore, 

do not fit into the Airbus ALI. United 

Airlines also states that, to date, it has 

not identified any cases of delamination 

on the elevators inspected by the same 

techniques in accordance with AD 

2002–18–01 and the ALI. United 

Airlines further states that Airbus has 

not reported any in-service incidents 

resulting from elevator aerodynamic 

limitations. 

NWA states that the tasks should be 

required by an AD-mandated service 

bulletin instead of including the tasks in 

the Airbus ALI. NWA asserts that the 

elevator water ingression resulted from 

a design problem that would more 

appropriately be managed through the 

service bulletin process. NWA states 

that including the tasks in the ALI 

document diminishes visibility of the 

unsafe condition and avoids 

coordination between the manufacturer 

and operators in identifying the scope 

and corrective actions for the unsafe 

condition. NWA also states that 

including the tasks into the ALI 

document increases the risk of record 

retention and compliance issues. NWA 

further states that inclusion of nonfatigue-based inspections for easily 

removable parts into the Airbus ALI 

could potentially change NWA’s 

maintenance program. NWA asserts that 

safety items of this complexity demand 

rigorous and thorough review prior to 

implementation, which can best be 

achieved through the airworthiness 

concern coordination process that has 

been successfully used for years by the 

industry. 

We do not agree to exclude ALI Tasks 

552007–01–1 and 552007–01–2 from the 

requirements of this AD. The 

commenters have not provided any data 

to indicate that these inspections are not 

effective, or that there is no unsafe 

condition. In addition, section 25.571 of 

the Federal Aviation Regulations (14 

CFR 25.571) does not differentiate 

between removable and non-removable 

structures, and tracking elevator time 

would be required regardless of whether 

the problem was addressed by a service 

bulletin or the Airbus ALI. Although we 

agree that the ALIs primarily deal with 

fatigue issues, FAA Advisory Circular 

20–107A, ‘‘Composite Aircraft 

Structure,’’ dated April 25, 1984, states 

that the effects of temperature, 

humidity, and other environmental 

factors that might result in material 

property degradation should be 

addressed in the damage tolerance 

evaluation. Water ingress in the elevator 

structure is clearly an environmental 

factor that could result in an unsafe 

condition. Operators were given due 

process by publication of the NPRM and 

the Airbus ALI. Therefore, we have not 

changed this AD in this regard. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been received, and determined 

that air safety and the public interest 

require adopting the AD with the 

changes described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 


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56264 Federal Register / Vol. 72, No. 191 / Wednesday, October 3, 2007 / Rules and Regulations 

Costs of Compliance 

The following table provides the 

estimated costs, at an average labor rate 

of $80 per hour, for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work 

hours 

Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

ALS revision(required by AD 2005–02–09) ................................................................. 1 $80 720 $57,600 

ALS revision (new action) ............................................................................................ 1 80 720 57,600 

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 AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 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, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 39–13450 (69 

FR 5909, February 9, 2004) and 

amendment 39–13954 (70 FR 3871, 

January 27, 2005) and by adding the 

following new airworthiness directive 

(AD): 

2007–20–05 Airbus: Amendment 39–15215. 

Docket No. FAA–2007–27015; 

Directorate Identifier 2006–NM–169–AD. 

Effective Date 

(a) This AD becomes effective November 7, 

2007. 

Affected ADs 

(b) This AD supersedes AD 2004–03–06 

and AD 2005–02–09. 

Applicability 

(c) This AD applies to all Airbus Model 

A318–111, A318–112, A319, A320, and A321 

airplanes, certificated in any category. 

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 according 

to paragraph (l) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25.1529–1. 

Unsafe Condition 

(d) This AD results from issuance of new 

and more restrictive service life limits and 

structural inspections based on fatigue 

testing and in-service findings. We are 

issuing this AD to detect and correct fatigue 

cracking, accidental damage, or corrosion in 

principal structural elements and to prevent 

failure of certain life limited parts, 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 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 

2005–02–09 

Revise Airworthiness Limitations Section 

(ALS) 

(f) For all Model A319, A320, and A321 

airplanes: Within 6 months after March 3, 

2005 (the effective date of AD 2005–02–09), 

revise the ALS of the Instructions for 

Continued Airworthiness in accordance with 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the Direction 

Ge ́ne ́rale de l’Aviation Civile (DGAC) (or its 

delegated agent); or the European Aviation 

Safety Agency (EASA) (or its delegated 

agent). One approved method of compliance 

is incorporating Airbus A318/A319/A320/ 

A321 Maintenance Planning Document 

(MPD), sub-Section 9–1–2, ‘‘Life Limited 

Parts,’’ and sub-Section 9–1–3, 

‘‘Demonstrated Fatigue Life Parts,’’ both 

Revision 06, both dated June 13, 2003. 

Note 2: Airbus Service Information Letter 

32–098, dated December 22, 2003, may be 

used as a source of service information for 

managing life limited and demonstrated 

fatigue life parts that were not previously 

tracked. 

(g) For all Model A319, A320, and A321 

airplanes; except Model A319 airplanes on 

which Airbus Modifications 28238, 28162, 

and 28342 were incorporated during 

production: Within 6 months after March 3, 

2005, revise the ALS of the Instructions for 

Continued Airworthiness in accordance with 

a method approved by the Manager, 

International Branch, ANM–116; or the 


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DGAC (or its delegated agent); or the EASA 

(or its delegated agent). One approved 

method of compliance is incorporating both 

Airbus A318/A319/A320/A321 MPD, subSection 9–2, ‘‘Airworthiness Limitation 

Items,’’ Revision 06, dated June 13, 2003; and 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Items (ALIs), 

Document AI/SE–M4/95A.0252/96, Issue 6, 

dated May 15, 2003 (approved by the DGAC 

on July 15, 2003). 

New Requirements of This AD 

Revise ALS To Incorporate Safe Life ALIs 

(h) For all airplanes: Within 3 months after 

the effective date of this AD, revise the ALS 

of the Instructions for Continued 

Airworthiness to incorporate Sub-part 1–2, 

‘‘Life Limits,’’ and Sub-part 1–3, 

‘‘Demonstrated Fatigue Lives,’’ of Airbus 

A318/A319/A320/A321 ALS Part 1—Safe 

Life Airworthiness Limitation Items, dated 

February 28, 2006 (hereafter referred to as 

‘‘ALS Part 1’’). Accomplish the actions in 

ALS Part 1 at the times specified in ALS Part 

1, except as provided by paragraph (j) of this 

AD. For Model A319, A320, and A321 

airplanes, accomplishing the revision in this 

paragraph terminates the requirements of 

paragraph (f) of this AD. 

Revise ALS To Incorporate Damage-Tolerant 

ALIs 

(i) For all airplanes, except Model A319 

airplanes on which Airbus Modifications 

28238, 28162, and 28342 have been 

incorporated in production: Within 14 days 

after the effective date of this AD, revise the 

ALS of the Instructions for Continued 

Airworthiness to incorporate Airbus A318/ 

A319/A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/95A.0252/96, 

Issue 7, dated December 2005 (approved by 

the EASA on February 7, 2006) (hereafter 

referred to as ‘‘Issue 7 of the ALI’’); Issue 08, 

dated March 2006 (approved by the EASA on 

January 4, 2007) (hereafter referred to as 

‘‘Issue 08 of the ALI’’); or Issue 09, dated 

November 2006 (approved by the EASA on 

May 21, 2007) (hereafter referred to as ‘‘Issue 

09 of the ALI’’). Accomplish the actions in 

Issue 7, Issue 08, or Issue 09 of the ALI at 

the times specified in Issue 7, Issue 08, or 

Issue 09 of the ALI, as applicable, except as 

provided by paragraph (j) of this AD. For 

Model A319, A320, and A321 airplanes, 

accomplishing the revision in this paragraph 

terminates the requirements of paragraph (g) 

of this AD. 

Grace Period for New or More Restrictive 

Actions 

(j) For any new or more restrictive life limit 

introduced with ALS Part 1, replace the part 

at the time specified in ALS Part 1 or within 

6 months after the effective date of this AD, 

whichever is later. For any new or more 

restrictive inspection introduced with Issue 

7, Issue 08, or Issue 09 of the ALI, do the 

inspection at the time specified in Issue 7, 

Issue 08, or Issue 09 of the ALI, as applicable, 

or within 6 months after the effective date of 

this AD, whichever is later. 

No Alternative Life Limits, Inspections, or 

Inspection Intervals 

(k) After the actions specified in 

paragraphs (h) and (i) of this AD have been 

accomplished, no alternative life limits, 

inspections, or inspection intervals may be 

used, except as provided by paragraphs (j) 

and (l) of this AD. 

Alternative Methods of Compliance (AMOCs) 

(l)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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 

(m) EASA airworthiness directive 2006–

0162, dated June 8, 2006; and EASA 

airworthiness direction 2006–0165, dated 

June 13, 2006; also address the subject of this 

AD. 

Material Incorporated by Reference 

(n) You must use the service information 

identified in Table 1 of this AD, as 

applicable, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. 

TABLE 1.—MATERIAL INCORPORATED BY REFERENCE

Service information Revision/issue level Date 

Airbus A318/A319/A320/A321 ALS Part 1—Safe Life Airworthiness Limitation 

Items.

Revision 00 ........................................... February 28, 2006. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–

M4/95A.0252/96.

Issue 7 ................................................... December 2005. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–

M4/95A.0252/96.

Issue 08 ................................................. March 2006. 

Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE–

M4/95A.0252/96.

Issue 09 ................................................. November 2006. 

(Issue 7 of Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, contains the 

following errors: The Summary of Changes is 

comprised of 11 pages, which are all 

identified as Page 2—LEP of Section LEP 

instead of Page 1—SOC [through] Page 11—

SOC of Section SOC; the List of Effective 

Pages only refers to Page 1—SOC for the 

Summary of Changes. The List of Effective 

Pages is comprised of two pages, and both of 

those pages are identified as Page 2—LEP. 

The first page of Section 2 is identified as 

Page 6 of Section 1 and is not referred to in 

the List of Effective Pages. Issue 08 of Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE–M4/ 

95A.0252/96, contains the following errors: 

Pages 3—ROR and 2—SOC are not referred 

to in the List of Effective Pages. The List of 

Effective Pages are identified as Pages 1—

SOC and 2—SOC, instead of 1—LEP and 2—

LEP. The first page of Section 2 is identified 

as Page 6 of Section 1 and is not referred to 

in the List of Effective Pages.) The Director 

of the Federal Register approved the 

incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, for a copy of this service 

information. You may review copies at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or at 

the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 21, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–19208 Filed 10–2–07; 8:45 am] 

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