Airworthiness Directives; The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes

[Federal Register Volume 75, Number 164 (Wednesday, August 25, 2010)]
[Rules and Regulations]
[Pages 52242-52246]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-20556]


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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.

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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 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. For certain other airplanes, the existing AD 
requires that the inspections be done repetitively. Replacing the 
elevator tab control mechanism with a new Boeing-built 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:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 [email protected]; Internet 
https://www.myboeingfleet.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://

[[Page 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 non-Boeing-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 Boeing-built 
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-to-spacer interface. Boeing Alert Service 
Bulletin 737-27A1297, Revision 1, also removes the procedure to 
determine if replacement mechanisms are Boeing-built 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
------------------------------------------------------------------------
                                      Corresponding requirement in this
   Requirement in  AD 2010-09-05                      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-

[[Page 52244]]

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

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 39-16270 (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

[[Page 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 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 (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: [email protected]. 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: [email protected]. 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

[[Page 52246]]

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: [email protected].
    (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 
[email protected]; 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

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