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[Federal Register Volume 75, Number 79 (Monday, April 26, 2010)]
[Rules and Regulations]
[Pages 21499-21503]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-9692]

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Rules and Regulations
                                                Federal Register
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having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

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Federal Register / Vol. 75, No. 79 / Monday, April 26, 2010 / Rules 
and Regulations

[[Page 21499]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0430; Directorate Identifier 2010-NM-098-AD; 
Amendment 39-16270; AD 2010-09-05]
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 The Boeing Company Model 737-600, -700, -700C, 
-800, -900, and -900ER series airplanes. The existing AD currently 
requires doing a detailed inspection of the inboard and outboard aft 
attach lugs of the left and right elevator control tab mechanisms for 
gaps between the swage ring and the aft attach lug, and between the 
spacer and the aft attach lug; trying to move or rotate the spacer 
using hand pressure; and replacing any discrepant elevator tab control 
mechanism, including performing the detailed inspection on the 
replacement part before and after installation. For certain airplanes, 
this new AD adds improved repetitive inspections for discrepancies of 
the inboard and outboard aft attach lugs of the left and right elevator 
control tab mechanisms, and replacement if necessary. For certain other 
airplanes, this new AD adds a one-time inspection for discrepancies of 
the inboard and outboard aft attach lugs of the left and right elevator 
control tab mechanisms, and replacement if necessary. For airplanes on 
which the elevator control tab mechanism is replaced with a certain 
mechanism, this AD requires repetitive inspections for discrepancies of 
the elevator control tab mechanism and replacement if necessary. 
Replacing the elevator control tab mechanism with a new, Boeing-built 
mechanism terminates the repetitive inspections. This AD results from a 
report of failure of the aft attach lugs on the left elevator tab 
control mechanism, which resulted in severe elevator vibration; this 
event occurred on an airplane on which the existing AD had been done. 
We are issuing this AD to detect and correct a loose bearing in the aft 
lug 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.

DATES: This AD becomes effective April 29, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 29, 
2010.
    On April 7, 2010 (75 FR 16648, April 2, 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 June 10, 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://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 March 18, 2010, we issued AD 2010-06-51, amendment 39-16250 (75 
FR 16648, April 2, 2010). That AD applies to all The Boeing Company 
Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. 
That AD requires doing a detailed inspection of the inboard and 
outboard aft attach lugs of the left and right elevator control tab 
mechanisms for gaps between the swage ring and the aft attach lug, and 
between the spacer and the aft attach lug; trying to move or rotate the 
spacer using hand pressure; and replacing any discrepant elevator tab 
control mechanism, including performing the detailed inspection on the 
replacement part before and after installation. That AD resulted from a 
report of failure of the aft attach lugs on the left elevator tab 
control mechanism, which resulted in severe elevator vibration. The 
actions specified in that AD are intended to detect and correct a loose 
bearing in the aft lug 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 Was Issued

    Since we issued that AD, we received an additional report of 
failure of the aft attach lugs on the left elevator tab control 
mechanism. This event occurred on an airplane that had been inspected

[[Page 21500]]

in accordance with AD 2010-06-51. We have determined that an improved 
inspection is necessary to address the identified unsafe condition. We 
verified the inspection procedure with an operator prior to approval of 
Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 737-27A1297, dated 
April 16, 2010. The service bulletin describes procedures for Model 
737-700, -700C, -800, and -900ER series airplanes, line numbers 2508 
through 3250 inclusive. The service bulletin specifies a one-time 
detailed inspection (for all airplanes having line numbers 2708 through 
3250 inclusive that are approved for operation under ETOPS), and 
repetitive detailed inspections (for all airplanes having line numbers 
2508 through 2707 inclusive) for discrepancies of the inboard and 
outboard aft attach lugs of the left and right elevator control tab 
mechanisms, and replacing any discrepant mechanisms. The detailed 
inspection includes the use of a feeler gage and finger pressure and 
instructs to apply hand pressure during the inspection for gaps and 
looseness. Discrepancies include the following conditions:
     The spacer moves or rotates.
     Gap exists between the swage ring and the outer face of 
the aft attach lug such that a 0.005 inch feeler gage can be inserted 
more than 0.025 inch.
     Gap exists between two nested lugs such that a 0.005 inch 
feeler gage can be inserted more than 0.050 inch.
     Gap exists between the inner face of the aft attach lug 
and the spacer such that a 0.005 inch feeler gage can be inserted more 
than 0.050 inch.
    The service bulletin also specifies that for airplanes on which the 
elevator control tab mechanism is replaced with an elevator control tab 
mechanism that is not a Boeing-built mechanism, the repetitive detailed 
inspections described above are necessary.
    The service bulletin also specifies that replacing discrepant 
elevator control tab mechanisms with Boeing-built elevator control tab 
mechanisms eliminates the need for the repetitive inspections.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of these same type designs. For this reason, 
we are issuing this AD to supersede AD 2010-06-51. This new AD retains 
the inspection requirements of AD 2010-06-51, and also requires, for 
certain airplanes, accomplishing the actions specified in Boeing Alert 
Service Bulletin 737-27A1297, dated April 16, 2010, described 
previously, except as discussed under ``Differences Between the AD and 
Boeing Alert Service Bulletin 737-27A1297.'' This new AD also requires 
sending the inspection results to the manufacturer and sending 
discrepant elevator control tab mechanisms to the manufacturer.

Differences Between the AD and Boeing Alert Service Bulletin 737-
27A1297

    Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010, 
specifies that replacing discrepant elevator control tab mechanisms 
with Boeing-built elevator control tab mechanisms eliminates the need 
for the repetitive inspections. This AD specifies that installing only 
a new, Boeing-built elevator control tab mechanism terminates the 
repetitive inspections. We have not received sufficient data to 
demonstrate that repaired elevator control tab mechanisms were repaired 
using procedures that will adequately address the identified unsafe 
condition. We find that only allowing new Boeing elevator control tab 
mechanisms as terminating action, as specified by this AD, will 
adequately address the unsafe condition. We have coordinated this issue 
with Boeing.
    While Boeing Alert Service Bulletin 737-27A1297, dated April 16, 
2010, does not identify Model 737-600 and -900 series airplanes, this 
AD applies to those airplanes because they are subject to the Parts 
Installation paragraph of this AD.

Interim Action

    This AD is considered to be interim action. The inspection reports 
and the returned discrepant parts that are required by this AD will 
enable the airframe manufacturer and the FAA 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.

FAA's Justification and Determination of the Effective Date

    A loose bearing in the aft lug of the elevator tab control 
mechanism 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. 
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-2010-0430; Directorate Identifier 2010-NM-098-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

[[Page 21501]]

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

0
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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-16250 (75 FR 16648, April 2, 2010) and by adding 
the following new airworthiness directive (AD):

2010-09-05 The Boeing Company: Amendment 39-16270. Docket No. FAA-
2010-0430; Directorate Identifier 2010-NM-098-AD.

Effective Date

    (a) This AD becomes effective April 29, 2010.

Affected ADs

    (b) This AD supersedes AD 2010-06-51, Amendment 39-16250.

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 a report of failure of the aft attach 
lugs on the left elevator tab control mechanism, which resulted in 
severe elevator vibration; this event occurred on an airplane on 
which the existing AD had been done. The Federal Aviation 
Administration is issuing this AD to detect and correct a loose 
bearing in the aft lug 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.

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 2010-06-51

Inspection and Corrective Action

    (g) For Groups 1, 2, and 3; and Group 4, Configuration 2; as 
identified in Boeing Alert Service Bulletin 737-27A1296, dated March 
12, 2010: At the applicable time specified in paragraph 1.E. 
Compliance of Boeing Alert Service Bulletin 737-27A1296, dated March 
12, 2010, except as required by paragraph (i) of this AD, do a 
detailed inspection of the inboard and outboard aft attach lugs of 
the left and right elevator control tab mechanisms for gaps between 
the swage ring and the 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. 
Doing the inspection required by paragraph (m) or (o) of this AD, as 
applicable, terminates the requirements of this paragraph.
    (h) If, during accomplishment of the actions required by 
paragraph (g) of this AD, any gap is found between the swage ring 
and the aft attach lug, or between the spacer and the aft attach 
lug; or if the spacer moves or rotates: Before further flight, do 
the actions required by paragraphs (h)(1) and (h)(2) of this AD, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-27A1296, dated March 12, 2010.
    (1) Inspect the replacement elevator tab control mechanism for 
discrepancies, as specified in paragraph (g) of this AD; and, if no 
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 737-27A1296, 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 April 7, 2010 (the effective 
date of AD 2010-06-51).

Inspection Done According to Multi Operator Message (MOM)

    (j) An inspection done before April 7, 2010, according to Boeing 
Multi Operator Message Number MOM-MOM-10-0159-01B, 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)(1) 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, 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 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 7, 2010: Submit 
the report within 10 days after the inspection.
    (2) If the inspection was done before April 7, 2010: Submit the 
report within 10 days after April 7, 2010.

Parts Installation Specified in AD 2010-06-51

    (l) For all airplanes: As of April 7, 2010, and until the 
effective date 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. As of the effective date of this AD, 
comply with paragraph (u) of this AD.

New Requirements of This AD

Repetitive Inspections for Group 1 Airplanes, as Identified in Boeing 
Alert Service Bulletin 737-27A1297, Dated April 16, 2010

    (m) For Group 1 airplanes, as identified in Boeing Alert Service 
Bulletin 737-27A1297, dated April 16, 2010: Except as required by 
paragraph (n) of this AD, within 12 days after the effective date of 
this AD, 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 until the replacement specified in paragraph (r) of 
this AD is done. Doing the initial inspection required by this 
paragraph terminates the requirements of paragraph (g) of this AD.
    (n) For Group 1 airplanes as identified in Boeing Alert Service 
Bulletin 737-27A1297, dated April 16, 2010: Beginning 7 days after

[[Page 21502]]

the effective date of this AD, no person may operate an airplane on 
an extended twin operations (ETOPS) flight unless the initial 
inspection required by paragraph (m) of this AD has been 
accomplished.

One-Time Inspection for Group 2, Configuration 1 Airplanes, as 
Identified in Boeing Alert Service Bulletin 737-27A1297, Dated April 
16, 2010

    (o) For Group 2, Configuration 1 airplanes as identified in 
Boeing Alert Service Bulletin 737-27A1297, dated April 16, 2010: 
Within 30 days after the effective date of this AD, 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 this paragraph terminates the 
requirements of paragraph (g) of this AD.

Corrective Actions

    (p) If, during any inspection required by paragraph (m), (o), or 
(q) of this AD, any discrepancy is found, before further flight, 
replace the elevator tab control mechanism by doing the actions 
specified in paragraphs (p)(1) and (p)(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 on another replacement elevator tab 
control mechanism.
    (2) Re-inspect the installed elevator tab control mechanism 
using the inspection procedure specified in paragraph (o) 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

    (q) 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 until the replacement 
specified in paragraph (r) of this AD is done.

Terminating Action

    (r) Replacing an elevator tab mechanism with a new, Boeing-built 
mechanism, as specified in paragraphs (r)(1) and (r)(2) of this AD, 
terminates the inspections required by paragraphs (m), (o), and (q) 
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 Boeing-built.

    (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 (o) of this 
AD.

Reporting

    (s) At the applicable time specified in paragraph (s)(1) or 
(s)(2) of this AD: Submit a report of any findings (positive and 
negative) of the first inspection required by paragraphs (m), (o), 
and (q) of this AD, and any positive findings from the repetitive 
inspections required by 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 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.

Return of Discrepant Parts

    (t) If, during any inspection required by paragraph (m), (o), or 
(q) of this AD, any discrepancy is found, and if the inspection was 
done on or after the effective date of this AD: Within 30 days after 
the inspection, return the discrepant elevator tab control 
mechanism, and include a copy of the inspection report sent to 
Boeing, as specified in paragraph (s) of this AD, to: Spares 
Distribution Center, Attention: Manager, Airline Support, Repair 
Overhaul and Exchange Services, SSA 111, Boeing Commercial Airplane 
Group, 2201 South 142nd Street, Door W10, Seatac, Washington, USA, 
98168.

Parts Installation

    (u) For all airplanes identified in paragraph (c) of this AD: As 
of the effective date of this AD, comply with the conditions 
specified in paragraphs (u)(1) and (u)(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 either paragraphs (p)(1) and (p)(2) of this 
AD, or in paragraphs (r)(1) and (r)(2) of this AD; and no 
discrepancies have been found.
    (2) An elevator tab control mechanism, part number 251A2430-(), 
that is not a new, Boeing-built elevator tab control mechanism may 
be installed, provided that the mechanism is inspected using the 
inspection procedures specified in paragraph (m) of this AD within 
300 flight hours after doing the installation, and that the 
inspection is repeated thereafter at the interval specified in 
paragraph (m) of this AD.

Alternative Methods of Compliance (AMOCs)

    (v)(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 refer to 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 2010-06-51 
are approved as AMOCs for the corresponding provisions of paragraph 
(g) or (l) of this AD.

Material Incorporated by Reference

    (w) You must use Boeing Alert Service Bulletin 737-27A1296, 
dated March 12, 2010; or Boeing Alert Service Bulletin 737-27A1297, 
dated April 16, 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, dated April 16, 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-
27A1296, dated March 12, 2010, on April 7, 2010 (75 FR 16648, April 
2, 2010).

[[Page 21503]]

    (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 April 19, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-9692 Filed 4-22-10; 4:15 pm]
BILLING CODE 4910-13-P
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