Document ID: FAA-2012-1068-0011
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2013-05-09T04:00Z

[Federal Register Volume 78, Number 90 (Thursday, May 9, 2013)]
[Rules and Regulations]
[Pages 27010-27015]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-10006]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1068; Directorate Identifier 2011-NM-073-AD; 
Amendment 39-17443; AD 2013-09-02]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding two existing airworthiness directives (AD) 
that apply to certain The Boeing Company Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes. Those ADs, for certain airplanes, 
currently require repetitive inspections of the flap track of the wing 
outboard flap, and corrective actions if necessary; and eventual rework 
of the flap track assembly and rear spar attachments. For certain 
airplanes, this new AD adds repetitive inspections, scheduled 
overhauls, correct alignment during installation, and repetitive 
maintenance of the flap track, and corrective actions if necessary. 
This new AD also adds airplanes to the applicability. This AD was 
prompted by reports that the work sequence and procedures used during 
installation of replacement tracks could cause loose or cracked tracks. 
We are issuing this AD to detect and correct cracking and damage in the 
flap track, which could cause loss of the outboard trailing edge flap 
and consequent reduced controllability of the airplane.

DATES: This AD is effective June 13, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of June 13, 
2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of April 
22, 2002 (67 FR 11891, March 18, 2002).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
January 2, 2001 (65 FR 78913, December 18, 2000).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket 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 address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6440; fax 
425-917-6590; email: nancy.marsh@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2000-25-07, Amendment 39-12041 (65 FR 78913, 
December 18, 2000); and AD 2002-05-07, Amendment 39-12675 (67 FR 11891, 
March 18, 2002). Those ADs apply to the specified products, and require 
repetitive inspections of the flap track of the wing outboard flap, and 
corrective actions if necessary; and eventual rework of the flap track 
assembly and rear spar attachments. The NPRM published in the Federal 
Register on October 10, 2012 (77 FR 61542). The NPRM proposed to retain 
all requirements of AD 2000-25-07 and AD 2002-05-07. For certain 
airplanes, the NPRM proposed to add repetitive inspections, scheduled 
overhauls, correct alignment during installation, and repetitive 
maintenance of the flap track, and corrective actions if necessary. 
This new AD also adds airplanes to the applicability.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 61542, October 10, 2012) and the FAA's response to each comment.

Concurrence

    Boeing and United concurred with the content of the NPRM (77 FR 
61542, October 10, 2012).

Request To Change Text of Paragraph (p)(3) of the NPRM (77 FR 61542, 
October 10, 2012)

    Alaska Airlines requested that we change the text of paragraph 
(p)(3) of the NPRM (77 FR 61542, October 10, 2012) to revise the 
descriptions of the inspection locations to be similar to the 
instructions included in Boeing 737 Non Destructive Test (NDT) Manual 
Part 6, 57-50-06. The commenter suggested that the existing wording in 
paragraph (p)(3) of the NPRM contradicts the instructions specified in 
Boeing 737 NDT Manual Part 6, 57-50-06.
    We disagree with the request to change the text of paragraph (p)(3) 
of this AD. The inspections specified in paragraph (p)(3) of this AD 
must be done in accordance with paragraph 3.B.3., ``Inspection--Track 
Webs and Flanges,'' of the Accomplishment Instructions of Boeing 
Service Bulletin 737-57A1271, Revision 3, dated February 13, 2012. The 
instructions for accomplishing the eddy current inspection required by 
paragraph (p)(3) of this AD are detailed in Boeing 737 NDT Manual Part 
6, 57-50-06, which is an additional source of guidance. There is no 
contradiction in the instructions. No change has been made to the AD in 
this regard.

Request for Revised Service Information

    Southwest Airlines requested that Boeing Service Bulletin 737-
57A1271, Revision 3, dated February 13, 2012, be revised to add missing 
necessary data to support the rework requirements of paragraphs (s) and 
(t) of the NPRM (77 FR 61542, October 10, 2012) for flap track part 
number (P/N) 65C34809-3. The commenter stated that paragraphs (s) and 
(t) of the NPRM require doing the corrective actions in accordance with 
Boeing Service Bulletin 737-57A1271, Revision 3, dated February 13, 
2012. The commenter also stated that Boeing Service Bulletin 737-
57A1271, Revision 3, dated February 13, 2012, provides repair data, but 
the commenter noted that not all repair data are provided for flap 
track P/N 65C34809-3. The commenter added that Boeing

[[Page 27011]]

Overhaul Manual 57-53-15, Figure 614, ``Supplemental Track Overhaul 
Instructions,'' should be revised to add minimum allowable dimensions 
T1 through T4, W, and maximum allowable hole diameters d1, d2, and d3 
for flap track P/N 65C34809-3.
    We disagree that any revised service information is necessary to 
comply with the requirements of this AD. While the repair data for flap 
track P/N 65C34809-3 is less extensive than for other tracks, the 
information provided in Boeing Service Bulletin 737-57A1271, Revision 
3, dated February 13, 2012, is adequate for this part. Since that flap 
track has improved finishes, it is not expected to wear in the same way 
as the other parts. If this flap track requires repair or rework that 
exceeds the data currently provided, then operators may request 
approval of new repair and rework limits in accordance with paragraph 
(y) of this AD. No change has been made to the AD in this regard.

Request To Extend Compliance Time

    Sky King, Inc. requested that we extend the compliance time from 
180 days to 24 months for airplanes with flap tracks that are 
undocumented or did not previously require inspection by AD 2000-25-07, 
Amendment 39-12041 (65 FR 78913, December 18, 2000); or AD 2002-05-07, 
Amendment 39-12675 (67 FR 11891, March 18, 2002). The commenter stated 
that extending the compliance time as requested will allow the operator 
to inspect the flap tracks at a more convenient interval, such as a 
scheduled ``C-check'' maintenance interval.
    We disagree with the request to extend the compliance time. The 
initial inspection compliance time of 180 days was selected to address 
potential safety issues on flap tracks that have not been inspected in 
accordance with AD 2000-25-07, Amendment 39-12041 (65 FR 78913, 
December 18, 2000); or AD 2002-05-07, Amendment 39-12675 (67 FR 11891, 
March 18, 2002). The commenter provided no data to support a request to 
extend the compliance time for these airplanes.
    In developing an appropriate compliance time for this AD, we 
considered not only the safety implications, but the manufacturer's 
recommendations and the practical aspect of accomplishing the 
inspection within an interval of time that corresponds to typical 
scheduled maintenance for affected operators. We consider that U.S. 
operators have had ample time to consider initiating the actions 
specified in Boeing Service Bulletin 737-57A1271, Revision 3, dated 
February 13, 2012, cited in the NPRM (77 FR 61542, October 10, 2012), 
which this AD ultimately requires. Under the provisions of paragraph 
(y) of this AD, however, we will consider requests for adjustments to 
the compliance time if data are submitted to substantiate that such an 
adjustment would provide an acceptable level of safety. No change has 
been made to the AD in this regard.

Effect of Supplemental Type Certificate (STC) for Winglet

    Aviation Partners Boeing stated that the installation of winglets 
per STC ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se) does 
not affect the accomplishment of the manufacturer's service 
instructions.
    We have added paragraph (c)(2) to this AD to state that 
installation of STC ST01219SE does not affect the ability to accomplish 
the actions required by this AD. Therefore, for airplanes on which STC 
ST01219SE is installed, a ``change in product'' alternative method of 
compliance (AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17. For all other AMOC requests, the operator 
must request approval in accordance with the procedures specified in 
paragraph (y) of this AD.

Other Changes to the AD

    We have removed table 1 to paragraph (g) from this AD; instead, we 
have included the subject part numbers in paragraphs (g)(4)(i) through 
(g)(4)(x) of this AD. This change does not affect the intent of that 
paragraph.
    We have revised the second to last sentence in paragraph (p) of 
this AD to add references to paragraphs (l) and (m) of this AD. 
Performing the inspections required by paragraph (p) of this AD 
terminates the requirements of paragraphs (g), (j), (l), (m), and (n) 
of this AD.
    We have revised paragraph (s) of this AD to clarify the 
requirements for a damaged or corroded anti-fret strip.
    We have revised paragraph (x)(3) of this AD to correct the service 
bulletin citation to Boeing Service Bulletin 737-57A1271, Revision 2, 
dated January 17, 2011.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 61542, October 10, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 61542, October 10, 2012).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 570 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                    Cost per        Number of
                    Action                                Labor cost               Parts cost        product        airplanes     Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed visual inspection [retained actions   6 work-hours x $85 per hour =                 $0            $510             290                $147,900.
 from existing AD 2000-25-07, Amendment 39-     $510.
 12041 (65 FR 78913, December 18, 2000)].
Detailed visual, HFEC, and ultrasonic          4 work-hours x $85 per hour =                  0            $340           1,100                $374,000.
 inspections [retained actions from existing    $340.
 AD 2002-05-07, Amendment 39[dash]12675 (67
 FR 11891, March 18, 2002)].

[[Page 27012]]

 
Detailed and eddy current inspections [new     82 work-hours x $85 per hour =                 0      $6,970 per             570           $3,972,900 per
 actions].                                      $6,970 per inspection cycle.                         inspection                        inspection cycle.
                                                                                                          cycle
Overhaul [new action]........................  70 work-hours x $85 per hour =            20,000     $25,950 per             570          $14,791,500 per
                                                $5,950 per overhaul cycle.                       overhaul cycle                          overhaul cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for labor cost for repair, and parts cost for repair and 
replacement for the on-condition actions specified in this AD. The 
labor cost of the replacement is $1,360 (16 work-hours x $85 per hour). 
We have no way of determining the number of aircraft that might need 
these repairs/replacements.

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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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 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 FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 2000); and AD 
2002-05-07, Amendment 39-12675 (67 FR 11891, March 18, 2002); and 
adding the following new AD:

2013-09-02 The Boeing Company: Amendment 39-17443; Docket No. FAA-
2012-1068; Directorate Identifier 2011-NM-073-AD.

(a) Effective Date

    This AD is effective June 13, 2013.

(b) Affected ADs

    This AD supersedes ADs 2000-25-07, Amendment 39-12041 (65 FR 
78913, December 18, 2000); and 2002-05-07, Amendment 39-12675 (67 FR 
11891, March 18, 2002).

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in 
any category.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01219SE is 
installed, a ``change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports that the work sequence and 
procedures used during installation of replacement tracks installed 
in accordance with AD 2000-25-07, Amendment 39-12041 (65 FR 78913, 
December 18, 2000); or AD 2002-05-07, Amendment 39-12675 (67 FR 
11891, March 18, 2002); could cause loose or cracked tracks. We are 
issuing this AD to detect and correct cracking and damage in the 
flap track, which could cause loss of the outboard trailing edge 
flap and consequent reduced controllability of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Repetitive Inspections

    This paragraph restates the inspections required by paragraph 
(a) of AD 2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 
2000), with added references to a terminating action. For Model 737-
100, -200, and -200C series airplanes on which the left- or right-
hand inboard flap tracks of the wing outboard flap have a part 
number (P/N) listed in paragraphs (g)(4)(i) through (g)(4)(x) of 
this AD: Do a detailed visual inspection to detect damage 
(corrosion, cracking) of the aft end of the left- and right-hand 
inboard flap tracks of the wing outboard flap, per Boeing All 
Operator Message (AOM) M-7200-00-01854, dated July 27, 2000, at the 
latest of the times specified in paragraphs (g)(1), (g)(2), and 
(g)(3) of this AD. Repeat the inspection thereafter at intervals not 
to exceed 1,200 flight cycles. Accomplishing the requirements of 
paragraph (p) of this AD terminates the requirements of this 
paragraph.
    (1) Within 30 days after January 2, 2001 (the effective date of 
AD 2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 2000)).
    (2) Within 1,200 flight cycles after the last documented 
inspection or overhaul of the aft end of each flap track.
    (3) Before the accumulation of 15,000 total flight cycles.

[[Page 27013]]

    (4) Boeing flap tracks subject to this AD are identified in 
paragraphs (g)(4)(i) through (g)(4)(x) of this AD.
    (i) P/N 65-46428-9.
    (ii) P/N 65-46428-15.
    (iii) P/N 65-46428-17.
    (iv) P/N 65-46428-19.
    (v) P/N 65-46428-21.
    (vi) P/N 65-46428-23.
    (vii) P/N 65-46428-25.
    (viii) P/N 65-46428-27.
    (ix) P/N 65-46428-33.
    (x) P/N 65-46428-35.

(h) Retained Definition

    This paragraph restates the definition specified by Note 2 of AD 
2000-25-07, Amendment 39-12041 (65 FR 78913, December 18, 2000). For 
the purposes of this AD, a detailed visual inspection is defined as: 
``An intensive visual examination of a specific structural area, 
system, installation, or assembly to detect damage, failure, or 
irregularity. Available lighting is normally supplemented with a 
direct source of good lighting at an intensity deemed appropriate by 
the inspector. Inspection aids such as a mirror, magnifying lenses, 
etc., may be used. Surface cleaning and elaborate access procedures 
may be required.''

(i) Retained Corrective Actions

    This paragraph restates the corrective actions required by 
paragraph (b) of AD 2000-25-07, Amendment 39-12041 (65 FR 78913, 
December 18, 2000), with added reference to the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA). If any 
damage (corrosion, cracking) is detected during any inspection 
required by paragraph (g) of this AD, before further flight, repair 
or rework the flap track per the ``Repair and Rework Instructions'' 
specified in Boeing AOM M-7200-00-01854, dated July 27, 2000. Where 
that AOM specifies that the manufacturer may be contacted for 
disposition of certain corrective actions (i.e., repair and/or 
rework of the flaps), this AD requires such repair and/or rework to 
be done using a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA; or using data meeting the type 
certification basis of the airplane approved by a Boeing Company 
designated engineering representative (DER) or the Boeing Commercial 
Airplanes ODA that has been authorized by the Manager, Seattle ACO, 
to make such findings. For a repair method to be approved by the 
ODA, the repair must meet the certification basis of the airplane, 
and the approval must specifically refer to this AD. For a repair 
method to be approved by the Manager, Seattle ACO, as required by 
this paragraph, the Manager's approval letter must specifically 
reference this AD.

(j) Retained Initial Inspections

    This paragraph restates the initial inspections required by 
paragraph (a) of AD 2002-05-07, Amendment 39-12675 (67 FR 11891, 
March 18, 2002), with added references to terminating action. For 
Model 737-100, -200, and -200C series airplanes with line numbers 
(L/N) 1 through 869 inclusive, and those airplanes with L/Ns 870 
through 1585 inclusive, which either still have their original flap 
tracks or which have had the original flap tracks replaced with 
certain tracks as specified in Boeing Service Bulletin 737-57A1249, 
Revision 1, including Appendix A, dated June 1, 2000; except 
airplanes on which any replacement flap tracks were installed as 
specified in Boeing Service Bulletin 737-57-1203, dated November 15, 
1990, or production equivalent: Within 6 months after April 22, 2002 
(the effective date of AD 2002-05-07, Amendment 39-12675 (67 FR 
11891, March 18, 2002)), accomplish the requirements of paragraphs 
(j)(1) and (j)(2) of this AD, according to Boeing Service Bulletin 
737-57A1249, Revision 1, including Appendix A, dated June 1, 2000. 
Accomplishing the requirements of paragraph (p) of this AD 
terminates the requirements of this paragraph.
    (1) Perform a detailed visual inspection for discrepancies 
(e.g., corrosion, or missing, damaged, or migrated anti-fret strips 
and tapered shims) of the rear spar attachments of the flap tracks.
    (2) Perform detailed visual, high frequency eddy current (HFEC), 
and ultrasonic inspections for cracking in the upper flange of the 
inboard track of each outboard flap at the rear spar attachments.

(k) Retained Credit for Certain Previous Actions

    This paragraph restates the credit for certain previously 
accomplished actions specified by Note 3 of AD 2002-05-07, Amendment 
39-12675 (67 FR 11891, March 18, 2002). This paragraph provides 
credit for the actions specified in paragraphs (j), (l), (m), and 
(n) of this AD, if those actions were performed before the effective 
date of this AD using Boeing Alert Service Bulletin 737-57A1249, 
including Appendix A, dated December 16, 1999, which is not 
incorporated by reference in this AD.

(l) Retained Repetitive Inspections of the Rear Spar Attachment of the 
Flap Tracks and Upper Flange of the Inboard Track of Each Outboard Flap 
at the Rear Spar Attachments

    This paragraph restates the repetitive inspections required by 
paragraph (b) of AD 2002-05-07, Amendment 39-12675 (67 FR 11891, 
March 18, 2002). For airplanes subject to the requirements of 
paragraph (j) of this AD: If no discrepancy is found during any 
inspection required by paragraph (j) of this AD, thereafter, repeat 
the inspections specified in paragraph (j) of this AD at intervals 
not to exceed 9 months, until the actions required by paragraph (m) 
or (p) of this AD have been accomplished.

(m) Retained Rework

    This paragraph restates the rework required by paragraph (c) of 
AD 2002-05-07, Amendment 39-12675 (67 FR 11891, March 18, 2002). For 
airplanes subject to the requirements of paragraph (j) of this AD: 
At the applicable time specified in paragraph (m)(1) or (m)(2) of 
this AD, accomplish rework of the flap track assembly and aft flap 
track attachments (including removal of the flap track; a detailed 
visual inspection for a missing, damaged, or migrated anti-fret 
strip and tapered shim of the rear spar attachments of the flap 
track; replacement of the anti-fret strip with a new aluminum anti-
fret strip (or installation of an aluminum strip if no strip is 
installed), as applicable; replacement of the tapered shim with a 
new shim (or installation of a shim if no shim is installed); eddy 
current and ultrasonic inspections for fatigue cracking of the flap 
tracks; a detailed visual inspection for corrosion of the flap 
tracks; and rework of attachment holes), including replacement of 
the flap tracks, as applicable, by accomplishing all actions 
specified in Part II of the Accomplishment Instructions of Boeing 
Service Bulletin 737-57A1249, Revision 1, including Appendix A, 
dated June 1, 2000. Do these actions according to the Accomplishment 
Instructions of Boeing Service Bulletin 737-57A1249, Revision 1, 
including Appendix A, dated June 1, 2000, except as provided by 
paragraph (o) of this AD. Accomplishment of the actions required by 
this paragraph terminates the repetitive inspections required by 
paragraph (l) of this AD. Accomplishing the requirements of 
paragraph (p) of this AD terminates the requirements of this 
paragraph.
    (1) If no discrepancy is found during any inspection required by 
paragraph (j) or (l) of this AD: Do the rework within 24 months 
after April 22, 2002 (the effective date of AD 2002-05-07, Amendment 
39-12675 (67 FR 11891, March 18, 2002)).
    (2) If any discrepancy is found during any inspection required 
by paragraph (j) or (l) of this AD: Do the rework prior to further 
flight.

(n) Retained Repetitive Inspections of the Upper Flange of the Inboard 
Track of Each Outboard Flap at the Rear Spar Attachments

    This paragraph restates the repetitive inspections required by 
paragraph (d) of AD 2002-05-07, Amendment 39-12675 (67 FR 11891, 
March 18, 2002). For Model 737-100, -200, -200C, -300, -400, and -
500 series airplanes, except airplanes on which any replacement flap 
tracks were installed as specified in Boeing Service Bulletin 737-
57-1203, dated November 15, 1990, or production equivalent: At the 
applicable time specified in paragraph (n)(1) or (n)(2) of this AD, 
and thereafter at least every 24 months, perform detailed visual, 
HFEC, and ultrasonic inspections for cracking in the upper flange of 
the inboard track of each outboard flap at the rear spar 
attachments, according to Part I of the Accomplishment Instructions 
of Boeing Service Bulletin 737-57A1249, Revision 1, including 
Appendix A, dated June 1, 2000. Accomplishing the requirements of 
paragraph (p) of this AD terminates the requirements of this 
paragraph.
    (1) For airplanes subject to paragraph (m) of this AD, do the 
inspections within 10 years after accomplishment of the rework 
according to paragraph (m) of this AD.
    (2) For airplanes other than those identified in paragraph 
(n)(1) of this AD, do the inspections within 10 years since the 
airplane's date of manufacture, or within 6 months after April 22, 
2002 (the effective date of AD 2002-05-07, Amendment 39-12675 (67 FR 
11891, March 18, 2002)), whichever occurs later.

[[Page 27014]]

(o) Retained Repair Instructions and Exception to Procedures in Service 
Information

    This paragraph restates the repair instructions and exception to 
procedures required by paragraph (e) of AD 2002-05-07, Amendment 39-
12675 (67 FR 11891, March 18, 2002). If any discrepancy is found 
during any action required by paragraph (j), (l), or (m) of this AD, 
and Boeing Service Bulletin 737-57A1249, Revision 1, including 
Appendix A, dated June 1, 2000, specifies to contact Boeing for 
appropriate action; or if any discrepancy is found during 
inspections according to paragraph (n) of this AD: Prior to further 
flight, repair according to a method approved by the Manager, 
Seattle ACO, FAA; or according to data meeting the type 
certification basis of the airplane approved by a Boeing DER or 
Boeing Company ODA, that has been authorized by the Manager, Seattle 
ACO, to make such findings. For a repair method to be approved by 
the ODA, the repair must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD. For a 
repair method to be approved by the Manager, Seattle ACO, as 
required by this paragraph, the approval letter must specifically 
reference this AD.

(p) New Inspection of Flap Track Web and Flanges

    For all airplanes: At the times specified in paragraph (q) of 
this AD, do the inspections specified in paragraphs (p)(1), (p)(2), 
(p)(3), and (p)(4) of this AD, and do all applicable corrective 
actions, in accordance with paragraph 3.B.3., ``Inspection--Track 
Webs and Flanges,'' of the Accomplishment Instructions of Boeing 
Service Bulletin 737-57A1271, Revision 3, dated February 13, 2012, 
except as required by paragraphs (r) and (v) of this AD. Performing 
these inspections terminates the requirements of paragraphs (g), 
(j), (l), (m), and (n) of this AD. Do all applicable corrective 
actions before further flight.
    (1) Detailed inspection for damage (cracks, nicks, corrosion 
pits, galling, pieces broken off) and stop-drill repairs along the 
full length of the upper and lower flanges of the flap track.
    (2) Detailed inspection for damage, cracking, and stop-drill 
repairs along the full length of the track webs.
    (3) Eddy current inspection for damage (including cracking) of 
the flap track web and flanges.
    (4) Inspection to determine the part number of the flap track 
assembly.

(q) New Compliance Time

    At the latest of the applicable times specified in paragraphs 
(q)(1), (q)(2), and (q)(3) of this AD, do the actions required by 
paragraph (p) of this AD.
    (1) Within 96 months since the flap track was new or overhauled, 
or prior to the accumulation of 15,000 flight cycles on the flap 
track since new or overhauled, whichever occurs first.
    (2) Within 180 days after the effective date of this AD.
    (3) Within 24 months after the most recent inspection was 
performed using Part 1 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-57A1249, including Appendix A, dated 
December 16, 1999; or Boeing Service Bulletin 737-57A1249, Revision 
1, including Appendix A, dated June 1, 2000.

(r) New Replacement

    If, during any inspection required by paragraph (p) of this AD, 
any flap track assembly having P/N 65-46428-31 or 65-46428-33 is 
found, before further flight, replace the flap track assembly with a 
new or serviceable flap track assembly, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 737-57A1271, 
Revision 3, dated February 13, 2012, except as required by paragraph 
(v) of this AD.

(s) New Inspections of Flap-to-Wing Attachment if Repairs Are Done or 
if No Damage Is Found in Flap Track Web and Flanges

    For airplanes on which no damage is found in the flanges or the 
web during any inspection required by paragraph (p) of this AD; and 
for airplanes on which a repair is done during any corrective action 
required by paragraph (p) of this AD: Before further flight, do the 
inspections specified in paragraphs (s)(1) through (s)(4) of this 
AD, and do all applicable related investigative and corrective 
actions, in accordance with paragraphs 3.B.4., ``Inspection--With 
Track-to-Wing Attachment Assembled,'' and 3.B.5., ``Inspection--With 
Track-to-Wing Attachment Disassembled,'' of the Accomplishment 
Instructions of Boeing Service Bulletin 737-57A1271, Revision 3, 
dated February 13, 2012, except as required by paragraph (v) of this 
AD. If, during the inspection required by paragraph (s)(1) of this 
AD, an anti-fret strip is not found installed, before further 
flight, do the related investigative actions specified in the 
Accomplishment Instructions of Boeing Service Bulletin 737-57A1271, 
Revision 3, dated February 13, 2012. If, during the inspection 
required by paragraph (s)(1) of this AD, an anti-fret strip is found 
with signs of damage or corrosion, before further flight, do all 
applicable corrective actions, including making and installing a new 
anti-fret strip, in accordance with paragraph 3.B.5., ``Inspection--
With Track-to-Wing Attachment Disassembled,'' of the Accomplishment 
Instructions of Boeing Service Bulletin 737-57A1271, Revision 3, 
dated February 13, 2012, except as required by paragraph (v) of this 
AD. Do all applicable related investigative and corrective actions 
before further flight.
    (1) Detailed inspection for signs of movement between the 
tapered shim and anti-fret strip, installation of the anti-fret 
strip, and corrosion of the tapered shim and anti-fret strip.
    (2) Detailed inspection for signs of movement, cracks and 
corrosion of the area where the track is attached to the wing rear 
spar.
    (3) High frequency eddy current inspection for cracking of the 
outboard edge of the track adjacent to the outboard attach bolt.
    (4) Ultrasonic inspection for cracking of the inner edge of the 
track adjacent to the outboard attach bolt.

(t) New Overhaul

    Within 10,000 flight cycles on the flap track or 48 months, 
whichever occurs first, after accomplishing the inspection required 
by paragraph (p) of this AD: Do an overhaul of the flap track, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-57A1271, Revision 3, dated February 13, 2012, except as 
required by paragraph (v) of this AD. Repeat the overhaul thereafter 
at intervals not to exceed 20,000 flight cycles on the flap track or 
96 months, whichever occurs first.

(u) New Post-Overhaul Inspections

    For airplanes on which any overhaul required by paragraph (t) of 
this AD is done: Do the inspections specified in paragraph (p) of 
this AD within 10,000 flight cycles on the flap track or 48 months 
after the most recent overhaul, whichever occurs first. Repeat the 
inspections specified in paragraph (p) of this AD thereafter at 
intervals not to exceed 10,000 flight cycles on the flap track or 48 
months, whichever occurs first; except that if an overhaul required 
by paragraph (t) of this AD is done, do the next inspection within 
10,000 flight cycles or 48 months, whichever occurs first, after the 
overhaul.

(v) Service Information Exception

    Where Boeing Service Bulletin 737-57A1271, Revision 3, dated 
February 13, 2012, specifies to contact Boeing for appropriate 
action: Before further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (y) of this 
AD.

(w) New Parts Installation Prohibition

    As of the effective date of this AD, no person may install a 
flap track assembly, P/N 65-46428-31 or 65-46428-33, on any 
airplane.

(x) New Credit for Previous Actions in Paragraphs (p) Through (t) of 
This AD

    This paragraph provides credit for the actions specified in 
paragraphs (p) through (t) of this AD, if those actions were 
performed before the effective date of this AD using the service 
bulletin specified in paragraph (x)(1), (x)(2), or (x)(3) of this 
AD.
    (1) Boeing Alert Service Bulletin 737-57A1271, dated September 
11, 2003, which is not incorporated by reference in this AD.
    (2) Boeing Service Bulletin 737-57A1271, Revision 1, dated July 
30, 2008, which is not incorporated by reference in this AD.
    (3) Boeing Service Bulletin 737-57A1271, Revision 2, dated 
January 17, 2011, which is not incorporated by reference in this AD.

(y) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
ACO, send it to the

[[Page 27015]]

attention of the person identified in the Related Information 
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (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 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 ADs 2000-25-07, 
Amendment 39-12041 (65 FR 78913, December 18, 2000); and 2002-05-07, 
Amendment 39-12675 (67 FR 11891, March 18, 2002); are approved as 
AMOCs for the corresponding requirements of this AD.

(z) Related Information

    For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6440; fax: 425-917-6590; email: nancy.marsh@faa.gov.

(aa) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
June 13, 2013.
    (i) Boeing Service Bulletin 737-57A1271, Revision 3, dated 
February 13, 2012.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
April 22, 2002 (67 FR 11891, March 18, 2002).
    (i) Boeing Service Bulletin 737-57A1249, Revision 1, including 
Appendix A, dated June 1, 2000.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
January 2, 2001 (65 FR 78913, December 18, 2000).
    (i) Boeing All Operator Message M-7200-00-01854, dated July 27, 
2000.
    (ii) Reserved.
    (6) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (7) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (8) You may view this 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on April 19, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-10006 Filed 5-8-13; 8:45 am]
BILLING CODE 4910-13-P