52242 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 

We are issuing this AD to prevent engine 

in-flight shutdown leading to loss of control 

of the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Before next flight after the effective date 

of this AD, identify the serial number (S/N) 

of each P/N 02–7210–11001R13, P/N 05– 

7211–K006001, and P/N 05–7211–K006002 

clutch assembly installed on the airplane. If 

the S/N matches one of those listed in 

Thielert Aircraft Engines GmbH Service 

Bulletin (SB) No. TM TAE 125–0021, dated 

June 9, 2010, or SB No. TM TAE 125–1011 

P1, dated June 9, 2010, as applicable to 

engine model, replace the clutch assembly 

within the following compliance times: 

(i) For engines with affected clutch 

assemblies that have accumulated 100 flight 

hours or more on the effective date of this 

AD, replace the clutch assembly before 

further flight. 

(ii) For engines with affected clutch 

assemblies that have accumulated less than 

100 flight hours on the effective date of this 

AD, replace the clutch assembly before 

accumulating 100 flight hours. 

Clutch Assembly Prohibition 

(2) After the effective date of this AD: 

(i) Do not install an engine having a clutch 

assembly that is listed by S/N in Thielert 

Aircraft Engines GmbH Service Bulletin (SB) 

No. TM TAE 125–0021, dated June 9, 2010, 

or SB No. TM TAE 125–1011 P1, dated June 

9, 2010; and 

(ii) Do not install any clutch assembly 

listed by S/N in Thielert Aircraft Engines 

GmbH Service Bulletin (SB) No. TM TAE 

125–0021, dated June 9, 2010, or SB No. TM 

TAE 125–1011 P1, dated June 9, 2010, into 

any engine. 

FAA AD Differences 

(f) This AD differs from the Mandatory 

Continuing Airworthiness Information 

(MCAI) and/or service information as 

follows: 

(1) EASA AD 2010–0111–E, dated June 10, 

2010 (corrected June 11, 2010) has separate 

compliance times for engines installed on 

twin-engine airplanes. This AD does not. 

(2) EASA AD 2010–0111–E, dated June 10, 

2010 (corrected June 11, 2010) allows a single 

ferry flight with conditions. This AD does 

not. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(h) Refer to MCAI EASA AD 2010–0111– 

E, dated June 10, 2010 (corrected June 11, 

2010), for related information. 

(i) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: alan.strom@faa.gov; telephone 

(781) 238–7143; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(j) You must use Thielert Aircraft Engines 

GmbH Service Bulletin No. TM TAE 125– 

0021, dated June 9, 2010, or SB No. TM TAE 

125–1011 P1, also dated June 9, 2010, to 

identify the affected clutch assemblies 

requiring replacement by this AD. 

(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 Thielert Aircraft Engines 

GmbH, Platanenstrasse 14 D–09350, 

Lichtenstein, Germany, telephone: +49– 

37204–696–0; fax: +49–37204–696–55; email: info@centurion-engines.com. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; 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 Burlington, Massachusetts, on 

August 16, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–21058 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–2010–0798; Directorate 

Identifier 2010–NM–174–AD; Amendment 

39–16413; AD 2010–17–19] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to all Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. The existing AD currently 

requires, for certain airplanes, a onetime detailed inspection of the inboard 

and outboard aft attach lugs of the left 

and right elevator tab control 

mechanisms for discrepancies, and 

replacement of any discrepant elevator 

tab control mechanism. For certain 

other airplanes, the existing AD requires 

that the inspections be done 

repetitively. Replacing the elevator tab 

control mechanism with a new Boeingbuilt mechanism terminates the 

repetitive inspections in the existing 

AD. This new AD requires that modified 

repetitive inspections be done on all 

airplanes, regardless of accomplishment 

of the terminating action specified in 

the existing AD. This AD results from 

reports of failure of the aft attach lugs 

on the elevator tab control mechanisms, 

which resulted in severe elevator 

vibration. This AD also results from 

reports of gaps in elevator tab control 

mechanisms and analysis that 

additional elevator tab control 

mechanisms might have bearings that 

will come loose. We are issuing this AD 

to detect and correct discrepancies in 

the aft attach lugs of the elevator tab 

control mechanism, which could result 

in elevator and tab vibration. 

Consequent structural failure of the 

elevator or horizontal stabilizer could 

result in loss of structural integrity and 

aircraft control. 

DATES: This AD becomes effective 

September 9, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 9, 2010. 

On April 29, 2010 (75 FR 21499, April 

26, 2010), the Director of the Federal 

Register approved the incorporation by 

reference of a certain other publication 

listed in the AD. 

We must receive any 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. 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

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Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 52243 

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 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 available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On April 19, 2010, we issued AD 

2010–09–05, amendment 39–16270 (75 

FR 21499, April 26, 2010). That AD 

applies to all Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. That AD requires, for certain 

airplanes, a one-time detailed 

inspection of the inboard and outboard 

aft attach lugs of the left and right 

elevator tab control mechanisms for 

discrepancies, and replacement of any 

discrepant elevator tab control 

mechanism (the replacement includes 

performing the detailed inspection on 

the replacement part before and after 

installation, and corrective actions if 

necessary). For certain other airplanes, 

that AD requires repetitive inspections 

for discrepancies of the inboard and 

outboard aft attach lugs of the left and 

right elevator tab control mechanisms, 

and replacement if necessary. For 

airplanes on which the elevator tab 

control mechanism is replaced with a 

certain mechanism, that AD requires 

repetitive inspections for discrepancies 

of the elevator tab control mechanism 

and replacement if necessary. Replacing 

the elevator tab control mechanism with 

a new Boeing-built mechanism 

terminates the repetitive inspections in 

that AD. That AD resulted from reports 

of failure of the aft attach lugs on the 

elevator tab control mechanisms, which 

resulted in severe elevator vibration. 

One event occurred on an airplane on 

which a previous AD (emergency AD 

2010–06–51, Amendment 39–16250 (75 

FR 16648, April 2, 2010)) had been 

done. The actions specified in AD 2010– 

09–05 are intended to detect and correct 

discrepancies in the aft attach lugs of 

the elevator tab control mechanism, 

which could result in unwanted 

elevator and tab vibration. Consequent 

structural failure of the elevator or 

horizontal stabilizer could result in loss 

of structural integrity and aircraft 

control. 

Actions Since AD 2010–09–05 Was 

Issued 

Since we issued AD 2010–09–05, we 

have received reports of gaps and loose 

bearings. For Boeing-built mechanisms, 

we received reports of gaps but no 

reports of loose bearings. Also, 

additional analysis has shown that nonBoeing-built mechanisms installed on 

airplanes having Line Number 2708 and 

subsequent might have bearings that 

will come loose. We have determined 

that the identified unsafe condition is 

related to the design of the elevator tab 

control mechanism. Therefore, all 

airplanes identified in the applicability 

of this AD must be repetitively 

inspected. In addition, installing a 

Boeing-built mechanism is no longer 

terminating action for the repetitive 

inspections. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 737–27A1297, Revision 

1, dated August 2, 2010. This service 

bulletin describes procedures for 

repetitive inspections for discrepancies 

of the inboard and outboard aft attach 

lugs of the left and right elevator tab 

control mechanisms, and replacement if 

necessary. We referred to Boeing Alert 

Service Bulletin 737–27A1297, dated 

April 16, 2010, as the appropriate 

source of service information for 

accomplishing certain required actions 

in AD 2010–09–05. Boeing Alert Service 

Bulletin 737–27A1297, Revision 1, no 

longer specifies that installing a Boeingbuilt mechanism ends the repetitive 

inspections. Boeing Alert Service 

Bulletin 737–27A1297, Revision 1, also 

modifies the inspection procedure by 

expanding the allowable gap depth in 

the lug-to-lug interface and the lug-tospacer interface. Boeing Alert Service 

Bulletin 737–27A1297, Revision 1, also 

removes the procedure to determine if 

replacement mechanisms are Boeingbuilt or non-Boeing-built. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design. For this reason, we are issuing 

this AD to supersede AD 2010–09–05. 

This new AD retains certain 

requirements of the existing AD. This 

AD also requires accomplishing the 

actions specified in Boeing Alert Service 

Bulletin 737–27A1297, Revision 1, 

dated August 2, 2010, described 

previously, except this AD does not 

require sending discrepant elevator tab 

control mechanisms to the 

manufacturer. This AD does require 

sending the inspection results to the 

manufacturer. 

Change to Existing AD 

This AD retains certain requirements 

of AD 2010–09–05. As a result, the 

corresponding paragraph identifiers 

have changed in this AD, as listed in the 

following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in 

AD 2010–09–05 

Corresponding requirement in this AD 

paragraph (m) paragraph (g) 

paragraph (n) paragraph (h) 

paragraph (o) paragraph (i) 

paragraph (p) paragraph (j) 

paragraph (q) paragraph (k) 

paragraph (r) paragraph (l) 

paragraph (s) paragraph (m) 

Interim Action 

This AD is considered to be interim 

action. The manufacturer is currently 

developing a terminating action that 

will address the unsafe condition 

identified in this AD. Once final action 

has been identified, we might consider 

further rulemaking. 

FAA’s Justification and Determination 

of the Effective Date 

Discrepancies, including loose 

bearings, in the aft attach lugs of the 

elevator tab control mechanism could 

result in elevator and tab vibration. 

Consequent structural failure of the 

elevator or horizontal stabilizer could 

result in loss of structural integrity and 

aircraft control. Because of our 

requirement to promote safe flight of 

civil aircraft and thus, the critical need 

to ensure the structural integrity of the 

airplane and the short compliance time 

involved with this action, this AD must 

be issued immediately. 

Because an unsafe condition exists 

that requires the immediate adoption of 

this AD, we find that notice and 

opportunity for prior public comment 

hereon are impracticable and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2010–0798; Directorate Identifier 2010– 

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52244 Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 

NM–174–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 

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 the 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 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 part 39 of the Federal 

Aviation Regulations (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 39–16270 (75 

FR 21499, April 26, 2010) and by adding 

the following new airworthiness 

directive (AD): 

2010–17–19 The Boeing Company: 

Amendment 39–16413. Docket No. 

FAA–2010–0798; Directorate Identifier 

2010–NM–174–AD. 

Effective Date 

(a) This AD becomes effective September 9, 

2010. 

Affected ADs 

(b) This AD supersedes AD 2010–09–05, 

Amendment 39–16270. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes; 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Unsafe Condition 

(e) This AD results from reports of failure 

of the aft attach lugs on elevator tab control 

mechanisms, which resulted in severe 

elevator vibration. This AD also results from 

reports of gaps in elevator tab control 

mechanisms and analysis that additional 

elevator tab control mechanisms might have 

bearings that will come loose. The Federal 

Aviation Administration is issuing this AD to 

detect and correct discrepancies in the aft 

attach lugs of the elevator tab control 

mechanism, which could result in elevator 

and tab vibration. Consequent structural 

failure of the elevator or horizontal stabilizer 

could result in loss of structural integrity and 

aircraft control. 

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 Certain Requirements of AD 

2010–09–05, With Revised Terminating 

Action 

Repetitive Inspections for Group 1 

Airplanes, as Identified in Boeing Alert 

Service Bulletin 737–27A1297, Dated April 

16, 2010 

(g) For Group 1 airplanes, as identified in 

Boeing Alert Service Bulletin 737–27A1297, 

dated April 16, 2010: Except as required by 

paragraph (h) of this AD, within 12 days after 

April 29, 2010 (the effective date of AD 

2010–09–05), do a detailed inspection for 

discrepancies of the inboard and outboard aft 

attach lugs of the left and right elevator 

control tab mechanisms, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–27A1297, dated 

April 16, 2010. Repeat the inspection 

thereafter at intervals not to exceed 300 flight 

hours. Doing the replacement specified in 

paragraph (l) of this AD before the effective 

date of this AD terminates the requirements 

of this paragraph. Doing the inspection 

required by paragraph (n) of this AD 

terminates the requirements of this 

paragraph. 

(h) For Group 1 airplanes as identified in 

Boeing Alert Service Bulletin 737–27A1297, 

dated April 16, 2010: Beginning 7 days after 

April 29, 2010, no person may operate an 

airplane on an extended twin operations 

(ETOPS) flight unless the initial inspection 

required by paragraph (g) of this AD has been 

accomplished. Doing the inspection required 

by paragraph (n) of this AD terminates the 

requirements of this paragraph. 

One-Time Inspection for Group 2, 

Configuration 1 Airplanes, as Identified in 

Boeing Alert Service Bulletin 737–27A1297, 

Dated April 16, 2010 

(i) For Group 2, Configuration 1 airplanes 

as identified in Boeing Alert Service Bulletin 

737–27A1297, dated April 16, 2010: Within 

30 days after April 29, 2010, do a one-time 

detailed inspection for discrepancies of the 

inboard and outboard aft attach lugs of the 

left and right elevator control tab 

mechanisms, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–27A1297, dated April 

16, 2010. Doing the inspection required by 

paragraph (n) of this AD terminates the 

requirements of this paragraph. 

Corrective Actions for Paragraphs (g), (i), 

and (k) of This AD 

(j) If, during any inspection required by 

paragraph (g), (i), or (k) of this AD, any 

discrepancy is found, before further flight, 

replace the elevator tab control mechanism 

by doing the actions specified in paragraphs 

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

(1) Do a detailed inspection for 

discrepancies of the replacement elevator tab 

control mechanism; and, if no discrepancy is 

found, install the replacement elevator tab 

control mechanism; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–27A1297, dated April 

16, 2010. If any discrepancy is found, then 

that elevator tab control mechanism cannot 

be installed and the actions specified in this 

paragraph must be done before further flight 

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Federal Register / Vol. 75, No. 164 / Wednesday, August 25, 2010 / Rules and Regulations 52245 

on another replacement elevator tab control 

mechanism. 

(2) Re-inspect the installed elevator tab 

control mechanism using the inspection 

procedure specified in paragraph (i) of this 

AD. 

Repetitive Inspections for Certain Group 2, 

Configuration 1 Airplanes, as Identified in 

Boeing Alert Service Bulletin 737–27A1297, 

Dated April 16, 2010 

(k) For Group 2, Configuration 1 airplanes 

as identified in Boeing Alert Service Bulletin 

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

which the elevator control tab mechanism is 

replaced with a mechanism other than a new, 

Boeing-built mechanism: Within 300 flight 

hours after doing the replacement, do a 

detailed inspection for discrepancies of the 

inboard and outboard aft attach lugs of the 

left and right elevator control tab 

mechanisms, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–27A1297, dated April 

16, 2010. Repeat the inspection thereafter at 

intervals not to exceed 300 flight hours. 

Doing the replacement specified in paragraph 

(l) of this AD before the effective date of this 

AD is terminating action for this paragraph. 

Doing the inspection required by paragraph 

(n) of this AD terminates the requirements of 

this paragraph. 

Terminating Action for Paragraphs (g), (i), 

and (k) of This AD, if Done Before the 

Effective Date of This AD 

(l) Replacing an elevator tab mechanism 

with a new, Boeing-built mechanism before 

the effective date of this AD, as specified in 

paragraphs (l)(1) and (l)(2) of this AD, 

terminates the inspections required by 

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

Replacement of the elevator tab control 

mechanism on or after the effective date of 

this AD does not terminate the inspections 

required by paragraphs (g), (i), and (k) of this 

AD. 

Note 1: Refer to paragraphs 3.B.7.b.(1)(a)(1) 

and 3.B.7.b.(1)(a)(2) of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

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

establish whether the mechanism is Boeingbuilt. 

(1) Do a detailed inspection for 

discrepancies of the new, Boeing-built 

replacement elevator tab control mechanism; 

and, if no discrepancy is found, install the 

replacement elevator tab control mechanism; 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–27A1297, dated April 16, 2010. If any 

discrepancy is found, then that elevator tab 

control mechanism cannot be installed and 

the actions specified in this paragraph must 

be done on another new, Boeing-built 

replacement elevator tab control mechanism. 

(2) Re-inspect the installed elevator tab 

control mechanism using the inspection 

procedure specified in paragraph (i) of this 

AD. 

Reporting for Paragraphs (g), (i), and (k) of 

This AD 

(m) At the applicable time specified in 

paragraph (m)(1) or (m)(2) of this AD: Submit 

a report of any findings (positive and 

negative) of the first inspection required by 

paragraphs (g), (i), and (k) of this AD, and any 

positive findings from the repetitive 

inspections required by paragraphs (g) and 

(k) of this AD, to Boeing Commercial 

Airplanes Group, Attention: Manager, Airline 

Support, e-mail: rse.boecom@boeing.com. 

The report must include the inspection 

results including a description of any 

discrepancies found, the airplane line 

number, and the total number of flight cycles 

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 

April 29, 2010: Submit the report within 10 

days after the inspection. 

(2) If the inspection was done before April 

29, 2010: Submit the report within 10 days 

after April 29, 2010. 

New Requirements of This AD 

Repetitive Inspections 

(n) At the applicable time specified in 

paragraph (n)(1), (n)(2), or (n)(3) of this AD: 

Do a detailed inspection for discrepancies of 

the inboard and outboard aft attach lugs of 

the left and right elevator tab control 

mechanisms, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–27A1297, Revision 1, 

dated August 2, 2010. For Groups 1 and 2 

airplanes identified in Boeing Alert Service 

Bulletin 737–27A1297, Revision 1, dated 

August 2, 2010, repeat the inspection 

thereafter at intervals not to exceed 300 flight 

hours, except as provided by paragraph (t)(2) 

of this AD. For Group 3 airplanes identified 

in Boeing Alert Service Bulletin 737– 

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

repeat the inspection thereafter at intervals 

not to exceed 1,800 flight hours, except as 

required by paragraphs (p) and (t)(2) of this 

AD. Doing the inspection specified in this 

paragraph terminates the requirements of 

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

(1) For Group 1 airplanes identified in 

Boeing Alert Service Bulletin 737–27A1297, 

Revision 1, dated August 2, 2010: Within 300 

flight hours after doing an inspection in 

accordance with Boeing Alert Service 

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

or within 30 days after the effective date of 

this AD, whichever occurs later. 

(2) For Group 2 airplanes identified in 

Boeing Alert Service Bulletin 737–27A1297, 

Revision 1, dated August 2, 2010: At the later 

of the times specified in paragraph (n)(2)(i) 

and (n)(2)(ii) of this AD. 

(i) Before the accumulation of 2,000 total 

flight cycles or 4,000 total flight hours, 

whichever occurs first. 

(ii) Within 14 days after the effective date 

of this AD. 

(3) For Group 3 airplanes identified in 

Boeing Alert Service Bulletin 737–27A1297, 

Revision 1, dated August 2, 2010: Within 180 

days or 1,800 flight hours after the effective 

date of this AD, whichever occurs first. 

Corrective Actions 

(o) If, during any inspection required by 

paragraph (n) or (p) of this AD, any 

discrepancy is found, before further flight, 

replace the elevator tab control mechanism 

by doing the actions specified in paragraphs 

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

(1) Do a detailed inspection for 

discrepancies of the replacement elevator tab 

control mechanism; and, if no discrepancy is 

found, install the replacement elevator tab 

control mechanism; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–27A1297, Revision 1, 

dated August 2, 2010. If any discrepancy is 

found, then that elevator tab control 

mechanism cannot be installed and the 

actions specified in this paragraph must be 

done before further flight on another 

replacement elevator tab control mechanism. 

(2) Re-inspect the installed elevator tab 

control mechanism using the inspection 

procedure specified in paragraph (n) of this 

AD. 

Reduced Repetitive Inspection Interval for 

Group 3 Airplanes, as Identified in Boeing 

Alert Service Bulletin 737–27A1297, 

Revision 1, on Which the Mechanism Is 

Replaced 

(p) For Group 3 airplanes as identified in 

Boeing Alert Service Bulletin 737–27A1297, 

Revision 1, dated August 2, 2010, on which 

the elevator tab control mechanism is 

replaced during the actions required by 

paragraph (o) of this AD: Within 300 flight 

hours after doing the replacement, do a 

detailed inspection for discrepancies of the 

inboard and outboard aft attach lugs of the 

replaced elevator tab control mechanism, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–27A1297, Revision 1, dated August 2, 

2010. Repeat the inspection of the replaced 

elevator tab control mechanism thereafter at 

intervals not to exceed 300 flight hours, 

except as provided by paragraph (t)(2) of this 

AD. 

Credit for Initial Inspection Done in 

Accordance With the Original Issue of the 

Service Bulletin 

(q) For Group 1 airplanes as identified in 

Boeing Alert Service Bulletin 737–27A1297, 

Revision 1, dated August 2, 2010: Inspections 

done in accordance with Boeing Alert 

Service Bulletin 737–27A1297, dated April 

16, 2010, are acceptable for compliance with 

only the initial inspection required by 

paragraph (n) of this AD. 

Reporting for Paragraphs (n) and (p) of This 

AD 

(r) At the applicable time specified in 

paragraph (r)(1) or (r)(2) of this AD: Submit 

a report of any findings (positive and 

negative) of the first inspection required by 

paragraphs (n) and (p) of this AD, except for 

airplanes on which a report required by 

paragraph (m) of this AD has been submitted, 

only submit positive findings; and submit a 

report of any positive findings from the 

repetitive inspections required by paragraphs 

(n) and (p) of this AD; to Boeing Commercial 

Airplanes Group, Attention: Manager, Airline 

Support, e-mail: rse.boecom@boeing.com. 

The report must include the inspection 

results including a description of any 

discrepancies found, the airplane line 

number, and the total number of flight cycles 

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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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