68548 Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules 

(10) Reinstall the seat on the seat rail. 

(i) Lift the seat into the airplane and place 

on the seat rail. 

(ii) Hold seat latch disengaged and slide 

the seat aft and then forward to re-engage 

rollers. 

(iii) Lower vertical adjusting seats to a 

comfortable height. 

(iv) Reattach seat belt/shoulder harness to 

the seat, if previously attached to the seat. 

(v) Reinstall the seat stops. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Wichita 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: Gary 

Park, Aerospace Engineer, ACE–118W, 

Wichita Aircraft Certification Office (ACO), 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946–4123; 

fax: (316) 946–4107. 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. 

(h) AMOCs approved for AD 87–20–03 R2 

are approved for this AD. 

Related Information 

(i) To view the AD docket, go to U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, or on 

the Internet at http://www.regulations.gov. 

Issued in Kansas City, Missouri on 

November 1, 2010. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–28158 Filed 11–5–10; 8:45 am] 

BILLING CODE 4910–13–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1045; Directorate 

Identifier 2010–NM–101–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed 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: 

One case of elevator servo-control 

disconnection has been experienced on an 

aeroplane of the A320 family. Investigation 

has revealed that the failure occurred at the 

servo-control rod eye-end. 

Further to this finding, additional 

inspections have revealed cracking at the 

same location on a number of other servocontrol rod eye-ends. In several cases, both 

actuators of the same elevator surface were 

affected. The root cause of the cracking has 

not yet been determined and tests are 

ongoing. 

A dual servo-control disconnection on the 

same elevator could result in an uncontrolled 

surface, the elevator surface being neither 

actuated nor damped, which could lead to 

reduced control of the aeroplane. 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 


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DATES: We must receive comments on 

this proposed AD by December 23, 

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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed 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. You 

may review copies of the referenced 

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. 

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 proposed 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: 

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–2010–1045; Directorate Identifier 

2010–NM–101–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 based on 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 August 7, 2009, we issued AD 

2009–17–04, amendment 39–15995 (74 

FR 41611, August 18, 2009). That AD 

corresponds to the European Aviation 

Safety Agency (EASA) AD 2008–0149, 

dated August 5, 2008, and requires a 

one-time inspection of the elevator 

servo-control rod eye-ends to detect 

cracking and in case of findings 

replacement of the cracked rod eye-end 

with a serviceable unit and readjusting 

the elevator servo-control. 

Since we issued AD 2009–17–04, the 

EASA, which is the Technical Agent for 

the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0046, 

dated March 19, 2010 (referred to after 

this as ‘‘the MCAI’’), to supersede EASA 

AD 2008–0149 to correct an unsafe 

condition for the specified products. 

The MCAI states: 

One case of elevator servo-control 

disconnection has been experienced on an 

aeroplane of the A320 family. Investigation 

has revealed that the failure occurred at the 

servo-control rod eye-end. 

Further to this finding, additional 

inspections have revealed cracking at the 

same location on a number of other servocontrol rod eye-ends. In several cases, both 

actuators of the same elevator surface were 

affected. The root cause of the cracking has 

not yet been determined and tests are 

ongoing. 

A dual servo-control disconnection on the 

same elevator could result in an uncontrolled 

surface, the elevator surface being neither 

actuated nor damped, which could lead to 

reduced control of the aeroplane. 

To address this unsafe condition, EASA 

AD 2008–0149 [which corresponds to FAA 

AD 2009–17–04] was issued to require a onetime inspection of the elevator servo-control 

rod eye-ends for aeroplanes which have 

accumulated more than 10,000 total Flight 

Cycles (FC) since aeroplane first flight and, 

in case of findings, the accomplishment of 

corrective actions. As a result of this onetime inspection campaign, a significant 

number of rod eye-ends have been found 

cracked. In addition, some cracks have been 

reported on rod eye-ends that had not yet 

accumulated the 10,000 FC of the established 

threshold. 

For the reason described above, this AD 

partially retains the initial inspection 

requirement of EASA AD 2008–0149, which 

is superseded, reduces the compliance time 

of the initial inspections and introduces a 

repetitive inspection program. 

The corrective actions include 

replacing any cracked rod eye-end with 

a serviceable unit and re-adjusting the 

elevator servo-control. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A320–27A1186, Revision 05, 

including Appendices 1 through 6, 

dated March 10, 2010. 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 Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This 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 proposed 

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 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 770 products of U.S. 

registry. 

The actions that are required by AD 

2009–17–04 and retained in this 

proposed AD take about 13 work-hours 

per product, at an average labor rate of 

$85 per work hour. Based on these 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
68550 Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules 

figures, the estimated cost of the 

currently required actions is $1,105 per 

product. 

We estimate that it would take about 

12 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$785,400, or $1,020 per product. 

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 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 this 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

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 FAA amends § 39.13 by 

removing amendment 39–15995 (74 FR 

41611, August 18, 2009) and adding the 

following new AD: 

Airbus: Docket No. FAA–2010–1045; 

Directorate Identifier 2010–NM–101–AD. 

Comments Due Date 

(a) We must receive comments by 

December 23, 2010. 

Affected ADs 

(b) This AD supersedes AD 2009–17–04, 

amendment 39–15995. 

Applicability 

(c) This AD applies to Airbus Model A318– 

111, –112, –121, and –122; A319–111, –112, 

–113, –114, –115, –131, –132, and –133; 

A320–111, –211, –212, –214, –231, –232, 

–233; and A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes; certificated 

in any category; all manufacturer serial 

numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

One case of elevator servo-control 

disconnection has been experienced on an 

aeroplane of the A320 family. Investigation 

has revealed that the failure occurred at the 

servo-control rod eye-end. 

Further to this finding, additional 

inspections have revealed cracking at the 

same location on a number of other servocontrol rod eye-ends. In several cases, both 

actuators of the same elevator surface were 

affected. The root cause of the cracking has 

not yet been determined and tests are 

ongoing. 

A dual servo-control disconnection on the 

same elevator could result in an uncontrolled 

surface, the elevator surface being neither 

actuated nor damped, which could lead to 

reduced control of the aeroplane. 

* * * * * 

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. 

Restatement of Requirements of AD 2009– 

17–04, With Reduced and Revised 

Compliance Times and Revised Service 

Information 

(g) Unless already done, do the following 

actions. 

(1) At the applicable times specified in 

paragraphs (g)(1)(i) and (g)(1)(ii) of this AD: 

Inspect both the left-hand and right-hand 

inboard elevator servo-control rod eye-ends 

for cracking, in accordance with the 

instructions of Airbus All Operators Telex 

(AOT) A320–27A1186, Revision 04, dated 

April 3, 2009; or the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–27A1186, Revision 05, dated 

March 10, 2010. As of the effective date of 

this AD, use only Airbus Mandatory Service 

Bulletin A320–27A1186, Revision 05, dated 

March 10, 2010. 

(i) For airplanes that have accumulated 

10,000 total flight cycles or more as of 

September 22, 2009 (the effective date of AD 

2009–17–04): At the later of the times 

specified in paragraphs (g)(1)(i)(A) and 

(g)(1)(i)(B) of this AD. 

(A) Within 1,500 flight cycles after 

September 22, 2009. 

(B) Within 1,500 flight cycles after 

accumulating 10,000 total flight cycles since 

first flight of the airplane. 

(ii) For airplanes that have accumulated 

less than 10,000 total flight cycles as of 

September 22, 2009: At the later of the times 

specified in paragraphs (g)(1)(ii)(A) and 

(g)(1)(ii)(B) of this AD. 

(A) Before the accumulation of 5,000 total 

flight cycles. 

(B) Within 20 months after the effective 

date of this AD but no later than before the 

accumulation of 11,500 total flight cycles. 

(2) At the applicable time specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: 

Inspect both the left-hand and right-hand 

outboard elevator servo-control rod eye-ends 

for cracking, in accordance with the 

instructions of Airbus AOT A320–27A1186, 

Revision 04, dated April 3, 2009; or the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–27A1186, 

Revision 05, dated March 10, 2010. As of the 

effective date of this AD, use only Airbus 

Mandatory Service Bulletin A320–27A1186, 

Revision 05, dated March 10, 2010. 

(i) For airplanes that have accumulated 

10,000 total flight cycles or more as of 

September 22, 2009: At the later of the times 

specified in paragraphs (g)(2)(i)(A) and 

(g)(2)(i)(B) of this AD. 

(A) Within 3,000 flight cycles after 

September 22, 2009. 

(B) Within 3,000 flight cycles after 

accumulating 10,000 total flight cycles since 

first flight of the airplane. 

(ii) For airplanes that have accumulated 

less than 10,000 total flight cycles as of 

September 22, 2009: At the later of the times 

specified in paragraphs (g)(2)(ii)(A) and 

(g)(2)(ii)(B) of this AD. 

(A) Before the accumulation of 7,500 total 

flight cycles. 

(B) Within 40 months after the effective 

date of this AD but no later than before the 

accumulation of 13,000 total flight cycles. 

(3) Submit a report of the findings of the 

inspection required by paragraphs (g)(1) and 


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Federal Register / Vol. 75, No. 215 / Monday, November 8, 2010 / Proposed Rules 68551 

(g)(2) of this AD to Airbus in accordance with 

the instructions of Airbus AOT A320– 

27A1186, Revision 04, dated April 3, 2009; 

or the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A320– 

27A1186, Revision 05, dated March 10, 2010; 

at the applicable time specified in paragraph 

(g)(3)(i) or (g)(3)(ii) of this AD. As of the 

effective date of this AD, use only Airbus 

Mandatory Service Bulletin A320–27A1186, 

Revision 05, dated March 10, 2010. 

(i) If the inspection was done after 

September 22, 2009: Submit the report 

within 40 days after the inspection. 

(ii) If the inspection was done before 

September 22, 2009: Submit the report 

within 40 days after September 22, 2009. 

New Requirements of This AD 

Actions 

(h) Repeat the inspections of the left-hand 

and right-hand inboard and outboard elevator 

servo-control rod eye-ends for cracking as 

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

this AD at the later of the times specified in 

paragraph (h)(1) or (h)(2) of this AD. Repeat 

the inspections thereafter at intervals not to 

exceed 5,000 flight cycles. 

(1) Within 5,000 flight cycles after the last 

inspection required by paragraph (g)(1) or 

(g)(2) of this AD as applicable. 

(2) Within 6 months after the effective date 

of this AD. 

(i) If any cracking is found during any 

inspection required by this AD, before further 

flight, accomplish all applicable corrective 

actions in accordance with the 

Accomplishment Instructions and figures of 

Airbus Mandatory Service Bulletin A320– 

27A1186, Revision 05, dated March 10, 2010. 

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

person may install on any airplane an 

elevator servo-control rod eye-end unless it is 

new or has been inspected in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A320– 

27A1186, Revision 05, dated March 10, 2010, 

with no crack findings. 

(k) Actions done before the effective date 

of this AD, in accordance with the service 

information specified in Table 1 of this AD 

are acceptable for compliance with the 

corresponding requirements of paragraphs 

(g)(1) and (g)(2) of this AD. 

TABLE 1—CREDIT SERVICE INFORMATION

Airbus AOT— Revision— Dated— 

A320–27A1186 ......................................................................................................................................................... Original June 23, 2008. 

A320–27A1186 ......................................................................................................................................................... 01 August 11, 2008. 

A320–27A1186 ......................................................................................................................................................... 02 March 30, 2009. 

A320–27A1186 ......................................................................................................................................................... 03 April 1, 2009. 

A320–27A1186 ......................................................................................................................................................... 04 April 3, 2009. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(l) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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. AMOCs approved 

previously in accordance with AD 2009–17– 

04, Amendment 39–15995, are approved as 

AMOCs for the corresponding provisions of 

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 

(m) Refer to MCAI EASA Airworthiness 

Directive 2010–0046, dated March 19, 2010; 

and Airbus Mandatory Service Bulletin 

A320–27A1186, Revision 05, dated March 

10, 2010; for related information. 

Issued in Renton, Washington, on October 

23, 2010. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–28172 Filed 11–5–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2010–1028; Airspace 

Docket No. 10–AGL–16] 

Proposed Amendment of Class E 

Airspace; Greensburg, IN 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E airspace at Greensburg, 

IN, to accommodate new Standard 

Instrument Approach Procedures (SIAP) 

for the Decatur County Memorial 

Hospital Heliport. The FAA is taking 

this action to enhance the safety and 

management of Instrument Flight Rules 

(IFR) operations at the heliport. 

DATES: 0901 UTC. Comments must be 

received on or before December 23, 

2010. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. You must 

identify the docket number FAA–2010– 

1028/Airspace Docket No. 10–AGL–16, 

at the beginning of your comments. You 

may also submit comments through the 

Internet at http://www.regulations.gov. 

You may review the public docket 

containing the proposal, any comments 

received, and any final disposition in 

person in the Dockets Office between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Office (telephone 1–800–647– 

5527), is on the ground floor of the 

building at the above address. 

FOR FURTHER INFORMATION CONTACT: 

Scott Enander, Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; telephone: 817–321– 

7716. 

SUPPLEMENTARY INFORMATION: 


emcdonald on DSK2BSOYB1PROD with PROPOSALS