52246 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 

and flight hours accumulated on the airplane. 

Under the provisions of the Paperwork 

Reduction Act (44 U.S.C. 3501 et seq.), the 

Office of Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 10 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 10 days after the effective date of this 

AD. 

No Return of Parts 

(s) Although Boeing Alert Service Bulletins 

737–27A1297, dated April 16, 2010; and 

Revision 1, dated August 2, 2010; specify to 

return the affected elevator tab control 

mechanism to the manufacturer, this AD 

does not require the return of the part to the 

manufacturer. 

Parts Installation 

(t) As of the effective date of this AD, 

comply with the conditions specified in 

paragraphs (t)(1) and (t)(2) of this AD. 

(1) No person may install an elevator tab 

control mechanism, part number 251A2430– 

( ), on any airplane, unless the mechanism 

has been inspected before and after 

installation using the inspection procedures 

specified in paragraphs (o)(1) and (o)(2) of 

this AD, and no discrepancies have been 

found. 

(2) An elevator tab control mechanism, part 

number 251A2430–( ), may be installed, 

provided that the inspection specified in 

paragraph (n) of this AD is done within 300 

flight hours after doing the installation, and 

that the inspection specified in paragraph (n) 

of this AD is repeated thereafter at intervals 

not to exceed 300 flight hours. 

Alternative Methods of Compliance 

(AMOCs) 

(u)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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: Kelly 

McGuckin, Aerospace Engineer, Systems and 

Equipment Branch, ANM–130S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 425– 

917–6490; fax 425–917–6590. Information 

may be e-mailed to: 9–ANM–Seattle-ACO– 

AMOC–Requests@faa.gov. 

(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 principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2010–09–05, 

amendment 39–16270, are approved as 

AMOCs for the corresponding provisions of 

paragraphs (g), (h), (i), (j), and (k) of this AD. 

Material Incorporated by Reference 

(v) You must use Boeing Alert Service 

Bulletin 737–27A1297, dated April 16, 2010; 

and Boeing Alert Service Bulletin 737– 

27A1297, Revision 1, dated August 2, 2010; 

as applicable; to do the actions required by 

this AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 737–27A1297, 

Revision 1, dated August 2, 2010, under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing Alert Service Bulletin 

737–27A1297, dated April 16, 2010, on April 

29, 2010 (75 FR 21499, April 26, 2010). 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

service information that is incorporated by 

reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on August 

11, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–20556 Filed 8–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0804; Directorate 

Identifier 2010–NM–163–AD; Amendment 

39–16420; AD 2010–18–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

A special detailed inspection of A318/ 

A319/A320/A321 elevators pre-modification 

35515 was introduced under ALI 

(Airworthiness Limitations Items) task 

552007 in the ALS (Airworthiness 

Limitations Section) part 2 * * * This ALI 

task has been introduced with an 

applicability defined at aeroplane 

modification level. 

* * * * * 

It has been reported that some elevators 

may have been moved from the aeroplane on 

which they were originally fitted to another 

aeroplane, * * *. Consequently, those 

elevators might not have been inspected 

within the applicable required time frame as 

per ALI task 552007 requirements. 

* * * * * 

The unsafe condition is structural 

failure of the elevators and consequent 

loss of control of the airplane. This AD 

requires actions that are intended to 

address the unsafe condition described 

in the MCAI. 

DATES: This AD becomes effective 

September 9, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 9, 2010. 

We must receive comments on this 

AD by October 12, 2010. 

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. 

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Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 52247 

• 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 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0091, 

dated May 19, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

A special detailed inspection of A318/ 

A319/A320/A321 elevators pre-modification 

35515 was introduced under ALI 

(Airworthiness Limitations Items) task 

552007 in the ALS (Airworthiness 

Limitations Section) part 2 under ALI 

Document reference AI/SE–M4/95A.0252/96 

at issue 7; approved by EASA on 07 

February, 2006, and mandated by EASA AD 

2006–0165 [which corresponds to FAA AD 

2007–20–05, Amendment 39–15215 (72 FR 

56262, October 3, 2007)]. This ALI task has 

been introduced with an applicability 

defined at aeroplane modification level. 

A specific statement related to the 

interchangeable parts policy was introduced 

in issue 9 of the ALI Document approved by 

EASA on 21 May, 2007. This statement 

required to track interchangeable damage 

tolerant part movements between aeroplanes. 

It has been reported that some elevators 

may have been moved from the aeroplane on 

which they were originally fitted to another 

aeroplane, and spare parts may have been 

installed without being traced with regard to 

the ALI Document requirements. 

Consequently, those elevators might not have 

been inspected within the applicable 

required time frame as per ALI task 552007 

requirements. 

For the reasons described above, this AD 

requires the identification of the elevators 

installed on the aeroplane to determine 

whether these elevators have been inspected 

within the applicable required time frame as 

per ALI task 552007. If this had not been 

done, this AD requires the accomplishment 

of that inspection and, depending on 

findings, associated corrective action(s). 

The unsafe condition is structural 

failure of the elevators and consequent 

loss of control of the airplane. The 

corrective actions include a special 

detailed inspection (thermographic) of 

affected elevators for damage, including 

cracking, and repairing any damage or 

cracking found. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–55A1040, dated January 11, 2010. 

Airbus has also issued A318/A319/ 

A320/A321 Airworthiness Limitation 

Items (ALI) AI/SE–M4/95A.0252/96, 

Issue 09, dated November 2006; and 

Issue 10, dated October 2009. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because some elevators may have 

been moved from one airplane to 

another without being traced, and 

consequently may not have been 

inspected in accordance with ALI task 

552007. Elevators not inspected within 

the compliance time in ALI Task 552007 

could fail. Failure of the elevators could 

result in reduced structural integrity of 

the airplane. Therefore, we determined 

that notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2010–0804; 

Directorate Identifier 2010–NM–163– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

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 

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52248 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 

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 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 this AD: 

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 AD and placed it in the AD docket. 

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 FAA amends § 39.13 by adding 

the following new AD: 

2010–18–07 Airbus: Amendment 39–16420. 

Docket No. FAA–2010–0804; Directorate 

Identifier 2010–NM–163–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 9, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A318–111, –112, –121, and –122 airplanes; 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

A special detailed inspection of A318/ 

A319/A320/A321 elevators pre-modification 

35515 was introduced under ALI 

(Airworthiness Limitations Items) task 

552007 in the ALS (Airworthiness 

Limitations Section) part 2 * * * This ALI 

task has been introduced with an 

applicability defined at aeroplane 

modification level. 

* * * * * 

It has been reported that some elevators 

may have been moved from the aeroplane on 

which they were originally fitted to another 

aeroplane, * * *. Consequently, those 

elevators might not have been inspected 

within the applicable required time frame as 

per ALI task 552007 requirements. 

* * * * * 

The unsafe condition is structural failure of 

the elevators and consequent loss of control 

of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 30 days after the effective date 

of this AD, inspect the left-hand (LH) and 

right-hand (RH) elevators to determine if the 

first twelve digits of the part number on the 

elevator are identified in Table 1 or Table 2 

of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–55A1040, dated 

January 11, 2010; and do the actions required 

by paragraphs (g)(1) and (g)(2) of this AD, as 

applicable. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number of the elevators 

can be conclusively identified from that 

review. 

(1) If any part number is identified in Table 

1 of this AD: Within 30 days after the 

effective date of this AD, do the applicable 

determination specified in paragraph (g)(1)(i) 

or (g)(1)(ii) of this AD and compare it to the 

threshold for the next due inspection, as 

specified in Airbus ALI Task 552007–01–1 or 

552007–01–3, which is defined in Airbus 

A318/A319/A320/A321 ALI AI/SE–M4/ 

95A.0252/96, Issue 09, dated November 

2006; or Issue 10, dated October 2009. 

TABLE 1—ELEVATOR PART NUMBER

Part name First twelve digits of 

part number only 

LH Elevator ............... D55280001000. 

RH Elevator ............... D55280001001. 

(i) For elevators on which Airbus Service 

Bulletin A320–55–1024 has been done: If 

adequate records exist, determine the elapsed 

(calendar) time since the date of the first 

flight of the first airplane on which the 

elevator is installed after the actions in 

Airbus Service Bulletin A320–55–1024 were 

done on the elevator. 

(ii) For elevators on which Airbus Service 

Bulletin A320–55–1024 has not been done: If 

adequate records exist, determine the elapsed 

(calendar) time since the date of the first 

flight of the first airplane on which the 

elevator is installed. 

(2) If any part number is identified in Table 

2 of this AD: Within 30 days after the 

effective date of this AD, if adequate records 

exist, determine the elapsed (calendar) time 

since the date of the first flight of the first 

airplane on which the elevator is installed 

and compare it to the threshold for the next 

due inspection, as specified in Airbus ALI 

Task 552007–01–2 or 552007–01–4, which is 

defined in Airbus A318/A319/A320/A321 

ALI AI/SE–M4/95A.0252/96, Issue 09, dated 

November 2006; or Issue 10, dated October 

2009. 

TABLE 2—ELEVATOR PART NUMBER

Part name First twelve digits of 

part number only 

LH Elevator ............... D55280001002, 

D55280001004, 

D55280001008, 

D55280001010, or 

D55280001012. 

RH Elevator .............. D55280001003, 

D55280001005, 

D55280001009, 

D55280001011 or 

D55280001013. 

(h) If the elapsed time, determined as 

required by paragraph (g)(1) of this AD, has 

exceeded the ALI threshold for the next due 

inspection, as specified in Airbus ALI Task 

552007–01–1 or 552007–01–3; or if unable to 

determine the elapsed time: Within 30 days 

after the effective date of this AD, perform a 

special detailed inspection for damage, 

including cracking, of the top and bottom 

skin panels of the affected elevators, in 

accordance with Airbus ALI Task 552007– 

01–1 or 552007–01–3, which is defined in 

Airbus A318/A319/A320/A321 ALI AI/SE– 

M4/95A.0252/96, Issue 09, dated November 

2006; or Issue 10, dated October 2009. If any 

damage or cracking is found, before further 

flight, repair 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). 

(i) If the elapsed time, determined as 

required by paragraph (g)(1) of this AD, has 

not exceeded the ALI threshold for the next 

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due inspection, as specified in Airbus ALI 

Task 552007–01–1 or 552007–01–3: Before 

reaching that threshold, or within 30 days 

after the effective date of this AD, whichever 

occurs later; perform a special detailed 

inspection for damage, including cracking, of 

the top and bottom skin panels of the affected 

elevators in accordance with Airbus ALI Task 

552007–01–1 or 552007–01–3, which is 

defined in Airbus A318/A319/A320/A321 

ALI AI/SE–M4/95A.0252/96, Issue 09, dated 

November 2006; or Issue 10, dated October 

2009. If any damage or cracking is found 

before further flight repair using a method 

approved by either the Manager, 

International Branch, or EASA (or its 

delegated agent). 

(j) If the elapsed time, determined as 

required by paragraph (g)(2) of this AD, has 

exceeded the ALI threshold for the next due 

inspection, as specified in Airbus ALI Task 

552007–01–2 or 552007–01–4; or if unable to 

determine the elapsed time: Within 30 days 

after the effective date of this AD, perform a 

special detailed inspection for damage, 

including cracking, of the top and bottom 

skin panels of the affected elevators, in 

accordance with Airbus ALI Task 552007– 

01–2 or 552007–01–4, which is defined in 

Airbus A318/A319/A320/A321 ALI AI/SE– 

M4/95A.0252/96, Issue 09, dated November 

2006; or Issue 10, dated October 2009. If any 

damage or cracking is found before further 

flight, repair using a method approved by 

either the Manager, International Branch, or 

the EASA (or its delegated agent). 

(k) If the elapsed time, determined as 

required by paragraph (g)(2) of this AD has 

not exceeded the ALI threshold for the next 

due inspection, as specified in Airbus ALI 

Task 552007–01–2 or 552007–01–4: Before 

reaching that threshold, or within 30 days 

after the effective date of this AD, whichever 

occurs later; perform a special detailed 

inspection for damage, including cracking, of 

the top and bottom skin panels of the affected 

elevators, in accordance with Airbus ALI 

Task 552007–01–2 or 552007–01–4, which is 

defined in Airbus ALI AI/SE–M4/95A.0252/ 

96, Issue 09, dated November 2006; or Issue 

10, dated October 2009. If any damage or 

cracking is found before further flight, repair 

using a method approved by either the 

Manager, International Branch, or EASA (or 

its delegated agent). 

(l) Accomplishment of the inspection and 

corrective actions required by paragraph (h), 

(i), (j), and (k) of this AD does not constitute 

terminating action for the repetitive 

inspections of Airbus ALI Task 552007, as 

defined in Airbus A318/A319/A320/A321 

ALI AI/SE–M4/95A.0252/96, Issue 09 dated 

November 2006; or Issue 10, dated October 

2009. 

(m) As of the effective date of this AD, no 

person may install, on any airplane, any 

elevator having a part number identified in 

Table 1 or 2 of this AD, unless the actions 

required by paragraphs (g)(1) and (g)(2), of 

this AD, as applicable, have been done and 

the inspections and corrective actions 

required by paragraphs (h), (i), (j), and (k) of 

this AD have been done. 

(n) As of the effective date of this AD, track 

all interchangeable damage tolerant part 

movements between airplanes, in accordance 

with the specific statement in the Section 

Rules for Compliance Demonstration, either 

in paragraph F., ‘‘Transferable Parts,’’ of the 

Airbus A318/A319/A320/A321 ALI AI/SE– 

M4/95A.0252/96, Issue 10, dated October 

2009; or in sub-paragraph 10., 

‘‘Interchangeable parts policy,’’ of Chapter 

1.11, ‘‘General Rules,’’ of Airbus A318/A319/ 

A320/A321 ALI AI/SE–M4/95A.0252/96, 

Issue 09, dated November 2006; or Issue 10, 

dated October 2009. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI or service information 

specifies to perform corrective actions using 

the instructions defined in Airbus ALI AI/ 

SE–M4/95A.0252/96, Issue 09, dated 

November 2006; or Issue 10, dated October 

2009; if any affected elevators are found, 

such corrective actions are not identified in 

the ALI tasks. Therefore, this AD requires 

that you perform all corrective actions before 

further flight 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). 

Other FAA AD Provisions 

(o) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): 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: Tim Dulin, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2141; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved; corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(p) Refer to MCAI EASA Airworthiness 

Directive 2010–0091, dated May 19, 2010; 

Airbus Service Bulletin A320–55A1040, 

dated January 11, 2010; and Airbus A318/ 

A319/A320/A321 ALI AI/SE–M4/95A.0252/ 

96, Issue 09, dated November 2006; and Issue 

10, dated October 2009; for related 

information. 

Material Incorporated by Reference 

(q) You must use the applicable service 

information specified in Table 3 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Document Issue Date 

Airbus A318/A319/A320/A321 Airworthiness Limitations Items AI/SE-M4/95A.0252/96 ............ 09 ................................ November 2006. 

Airbus A318/A319/A320/A321 Airworthiness Limitations Items AI/SE-M4/95A.0252/96 ............ 10 ................................ October 2009. 

Airbus Service Bulletin A320–55A1040 ....................................................................................... Original ........................ January 11, 2010. 

Airbus A318/A319/A320/A321 ALI AI/SE– 

M4/95A.0252/96, Issue 09, contains the 

following effective pages: 

Page title/description Page number(s) Issue 

No. Date shown on page(s) 

List of Effective Pages: 

ALI Title Page ........................................................................................... None shown .................................... 09 November 2006. 

Record of Revisions ................................................................................. 1–ROR through 3-ROR .................. 9 November 2006. 

Summary of Changes .............................................................................. 1–SOC through 2-SOC ................... 9 November 2006. 

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52250 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 

Page title/description Page number(s) Issue 

No. Date shown on page(s) 

List of Effective Pages ............................................................................. 1–LEP ............................................. 9 November 2006. 

Table of Contents ..................................................................................... 1–TOC ............................................ 9 November 2006. 

Section 1—Introduction ............................................................................ 1—7 ................................................ 9 November 2006. 

Section 2—Airworthiness Limitation Items (ALI) ...................................... 1—61 .............................................. 09 November 2006. 

Airbus A318/A319/A320/A321 ALI AI/SE– 

M4/95A.0252/96, Issue 10 contains the 

following effective pages: 

Page title/description Page number(s) Issue No. Date shown on page(s) 

List of Effective Pages: 

ALI Title Page ..................................................................... None shown ........................ 10 ........................................ October 2009. 

Record of Revisions ........................................................... 1–ROR through 4-ROR ....... None shown* ....................... October 2009. 

Table of Contents ............................................................... 1–TOC ................................. None shown* ....................... October 2009. 

Section 1—Introduction ...................................................... 1–INTRO through 8–INTRO None shown* ....................... October 2009. 

Section 2—Damage Tolerant Airworthiness Limitations 

List.

1—85 ................................... None shown* ....................... October 2009. 

Appendix A—Summary of Changes .................................. 1–APXA through 9-APXA ... None shown* ....................... October 2009. 

Appendix B—Abbreviations ................................................ 1–APXB through 2-APXB ... None shown* ....................... October 2009. 

Appendix C—Terms and Definitions .................................. 1–APXC ............................... None shown* ....................... October 2009. 

Appendix D—Reporting Form ............................................ 1–APXD ............................... None shown* ....................... October 2009. 

Appendix E—Modifications List .......................................... 1–APXE through 2-APXE ... None shown* ....................... October 2009. 

(*Only the title page of this document contains the issue level of the document.) 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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/ 

code_of_federal_regulations/ibr_

locations.html. 

Issued in Renton, Washington, on August 

13, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–21023 Filed 8–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0839; Directorate 

Identifier 2010–CE–042–AD; Amendment 

39–16418; AD 2010–18–05] 

RIN 2120–AA64 

Airworthiness Directives; Aircraft 

Industries a.s. (Type Certificate G24EU 

Previously Held by LETECKE ́ ZA ́ VODY 

a.s. and LET Aeronautical Works) 

Model L–13 Blanik Gliders 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above that will 

supersede an existing AD. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

A fatal accident occurred to a L–13 

BLANI ́K sailplane, in which the main spar of 

the right wing failed near the root due to 

positive load. The right wing detached from 

the aircraft and the pilots lost control of the 

sailplane. 

The preliminary investigation has revealed 

that the fracture may have been due to 

fatigue. 

The AD 2010–0119–E required immediate 

inspection of the main spar at the root of the 

wing to detect fatigue cracking and the 

accomplishment of the relevant corrective 

actions as necessary. In addition, the AD 

2010–0119–E imposed operational 

limitations. AD 2010–0122–E retained the 

requirements of AD 2010–0119–E, which is 

superseded, and extended the applicability to 

L–13 A BLANI ́K sailplanes. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

August 30, 2010. 

We must receive comments on this 

AD by October 12, 2010. 

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. 

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 

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