EMERGENCY AIRWORTHINESS DIRECTIVE

Aircraft Certification Service

Washington, DC

We post Emergency ADs on the internet at "www.faa.gov"

U.S. Department

of Transportation

Federal Aviation

Administration

ISSUE DATE: March 12,2010

AD 2010-06-51; Docket No. FAA-201 0-0230; Directorate Identifier 201 O-NM-071-AD

Emergency airworthiness directive (AD) 2010-06-51 is sent to all owners and operators of The

Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes.

Background

The FAA received a report of failure of the aft attach lugs on the left elevator tab control

mechanism, which resulted in severe elevator vibration. The flightcrew diverted from the intended

route and made an uneventful landing. Subsequent investigation revealed extensive damage to the

elevator tab control system. Severe vibration in this attach point is suspected of allowing rapid wear of

the joint, and resulted in failure of the attach lugs. This condition, if not corrected, could result in a

loss of aircraft control and structural integrity.

Explanation of Relevant Service lnformation

We have reviewed Boeing Alert Service Bulletin 737-27A1296, dated March 12,2010. The

service bulletin describes procedures for a detailed inspection to detect discrepancies of the inboard and

outboard aft attach lugs of the elevator tab control mechanism. Discrepancies include movement or

rotation of the spacer, and gaps between the swage ring and the aft attach lug or between the spacer and

the aft attach lug. The service bulletin describes procedures for replacing any discrepant elevator tab

control mechanism, including perfonning the detailed inspection on the replacement part before and

after installation. For certain airplanes, the compliance time for the inspeCtion is 12 or 30 days,

depending on airplane line number, total accumulated flight cycles, and approval for operation under

extended twin operations (ETOPS).

FAA's Determination and Requirements of this AD

We have evaluated all pertinent infomlation and identified an unsafe condition that is likely to

exist or develop on other airplanes of this same type design. Therefore, we are issuing this AD to

detect and correct a loose bearing in the aft lug oftbe eJevator tab control mechanism, which could

result in unwanted elevator and tab vibration. The consequent structural failure of the elevator or

horizontal stabilizer could result in loss of aircrall control and structural integrity. This AD requires

accomplishing the actions specified in the service information described previously, except as

discussed under "Differences Between this AD and the Service Bulletin." This AD also requires

reporting the JI1spection results to Boeing.
Differences Between this AD and the Service Bulletin

The effectivity of Boeing Alert Service Bulletin 737-27 A 1296, dated March 12, 20 I0, includes

all Model 737-600, -700, -700e, -800, -900, and -900ER series airplanes. The inspection requirements

of this AD, however, affect only those airplanes subject to a short compliance time (within 12 or 30

days). Because the suspect components may be installed as replacements on all airplanes subject to

this AD, paragraph (I) of this AD requires that the part be inspected before and after installation. We

may consider superseding this AD to apply the inspection requirements to the remaining airplanes,

which would be subject to a longer compliance time that would allow enough time to provide notice

and opportunity for prior public comment on the merits of the inspection for these airplanes.

Interim Action

This AD is considered to be interim action. The inspection reports that are required by this AD

will enable the manufacturer to obtain better insight into the nature, cause, and extent of the issue, and

eventually to develop final action to address the unsafe condition. Once final action has been

identified, we might consider further rulemaking.

Examining the Docket

You may examine the contents of this AD docket on the Internet at http://www.rcQulations.\!ov;

(on the next business day after we have issued the AD), or in person al U.S. Department of

Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New

Jersey Avenue SE., Washington, DC, between 9 a,m. and 5 p.m., Monday through Friday, except

Federal holidays. This docket number is FAA-2010-0230; the directorate identifier for this docket is

2010-NM-071-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 VIl,

Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle vn, Part A,

Subpart Ill, Section 44701, "General requirements," Under that section, Congress charges the FAA

with promoting safe night of civil aircraft in air commerce by prescribing regulations for practices,

methods, and procedures the Administrator fmds necessary for safety in air commerce. This regulation

is within the scope of that authority because it addresses an unsafe condition thal 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.

The FAA has determined that this regulation is an emergency regulation that must be issued

immediately to correct an unsafe condition in aircraft, and that it is not a "significant regulatory action"

under Executive Order 12866. It has been determined further that this action involves an emergency

regulation under DOT Regulatory Policies and Procedures (44 FR I 1034, February 26, 1979). If this

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emergency regulation is later deemed significant under DOT Regulatory Policies and Procedures, "ve

will prepare a final regulatory evaluation and place it in the AD Docket. See the "Examining the

Docket" section for a location to examine the regulatory evaluation, if filed.

Determination of Rule's Effective Date

This emergency AD is issued under 49 D.S.C. Section 44701 according to the authority

delegated to me by the Administrator, and is effective immediately upon receipt.

Because an unsafe condition exists that requires the immediate adoption of this emergency AD,

we find that notice and opportunity for prior public comment hereon are impracticable and that good

cause exists for making this emergency AD effective in less than 30 days.

2010-06-51 The Boeing Company: Docket No. FAA-2010-0230; Directorate Identifier

NO.2010-NM-071-AD.

Effective Date

(a) Emergency airworthiness directive (AD) 2010-06-51, issued on March 12,2010, is

effective immediately upon receipt.

Affected ADs

(b) None.

Applicability

(e) 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 a report offailure of the aft attach lugs on the left elevator tab control

mechanism, which resulted in severe elevator vibration. The Federal Aviation Administration is

issuing this AD to detect and conect a loose bearing in the aft lug of the elevator tab control

mechanism, which could result in unwanted elevator and tab vibration. The consequent structural

failure of the elevator or horizontal stabilizer could result in loss of aircraft control and structural

integrity.

Compliance

(f) You are responsible for having the actions required by this AD performed within the

compliance times specified, unless lhe actions have already been done.

Inspection and Corrective Action

(g) For Groups 1,2, and 3; and Group 4, ConfiguraLion 2; as identified in Boeing Alert Service

Bulletin 737-27 A 1296, dated March 12, 2010: At the applicable time specified in paragraph l.E.

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Compliance of Boeing Alert Service Bulletin 737-27 A 1296, dated March 12, 2010, except as required

by paragraph (i) of this AD, do a detailed inspection of tile inboard and outboard aft attach lugs of the

left and right elevator control tab mechanisms for gaps between the swage ring and tbe aft attach lug,

and between the spacer and the aft attach lug; and try to move or rotate the spacer using hand pressure,

in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1296,

dated March 12,2010.

(h) Lf,during accomplishment of the actions required by paragraph (g) oftbjs AD, any gap is

found between the swage ring and the aft attach lug, or behveen the spacer and the aft attach lug; or if

the spacer moves or rotates: Before further flight, do the actions required by paragraphs (h)(l) and

(h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service

Bulletin 737-27AI296, dated Mareh 12, 2010.

(1) Inspect the replacement elevator tab control mechanism for discrepancies, as specified in

paragraph (g) of this AD; and, ifno discrepancy is found, install the replacement elevator tab control

mechanism.

(2) Re-inspect the installed elevator tab control mechanism, as required by paragraph (g) of this

AD.

Exception to Service Bulletin Specifications

(i) Where Boeing Alert Service Bulletin 737-27 A 1296, dated March 12, 2010, specifies a

compliance time after the date of the original issue of the service bulletin, this AD requires compliance

within the specified compliance time after receipt of this AD.

Inspection Done According to Multi Operator Message (MOM)

(j) An inspection done before receipt of this AD according to Boeing Multi Operator Message

Number MOM-MOM-l 0-0 159-0 1B, dated March 10, 2010, is considered acceptable for compliance

with the corresponding inspection specified in paragraph (g) of this AD.

Reporting

(k) At the applicable time specified in paragraph (k)(l) or (k)(2) of this AD: Submit a report of

the findings (both positive and negative) of the inspections required by paragraph (g) of this AD to

Boeing Commercial Airplanes Group, Attention: Manager. Airline Support, email:

rse.boec.om@boeing.com. The report must include the inspection results including a description of any

discrepancies found, the airplane line number, and the number of flight cycles and flight hours

accumulated on the airplane. Under the provisions of tile Paperwork Reduction Act (44 U.S.c. 3501 et

seg.), the Office of Management and Budget (OMB) has approved the infomlalion collection

requirements contained in this AD and has assigned OMB Control Number 2120-0056.

(1) If the inspection was done on or after receipt of this AD: Submit the report within 10 days

after lhe inspection.

(2) Lfthe inspection was done before receipt of this AD: Submit the report within 10 days after

receipt of this AD.

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Parts Installation

(1) For all airplanes: As of receipt of this AD, 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, in accordance with the requirements of paragraph (g) of this AD, and no

discrepancies have been found.

Special Flight Permit

(m) Special flight permits, as described in Section 21.197 and Section 21.199 orthe Federal

Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed.

Alternative Methods of Compliance (AMOCs)

(n)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to

approve AMOCs for this AD, lfrequested using the procedures found in 14 eFR 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-AMOCReg uests({iihla.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 (PJ\1I) or principal avionics inspector

(PAT), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The

AMOC approval letter must specifically refer to this AD.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required

by this AD ifit 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.

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Contact Information

(0) For technical information about this AD, 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. For service infomlation

identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management,

P. O. Box 3707, Me 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, extension I;

fax 206-766-5680; c-mai Ime.boecom@boeing.com; Internet https:l/www.ll1vboeilH.,rfleeLcom.

$j2;hington, onMarch12,2010.

Ali Bahrami,

Manager,

Transport Airplane Directorate,

Aircraft Certification Service.

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