Document ID: FAA-2009-0452-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
Posted Date: 2009-05-20T04:00Z

[Federal Register: May 20, 2009 (Volume 74, Number 96)]
[Proposed Rules]               
[Page 23664-23668]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20my09-23]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0452; Directorate Identifier 2007-NM-326-AD]
RIN 2120-AA64

 
Airworthiness Directives; Boeing Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Boeing Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes. The existing AD currently 
requires a one-time inspection for scribe lines and cracks in the 
fuselage skin at certain lap joints, butt joints, external repair 
doublers, and other areas; and related investigative/corrective actions 
if necessary. This proposed AD would expand the area to be inspected 
and, for certain airplanes, require earlier inspections for certain 
inspection zones. This proposed AD results from additional detailed 
analysis of fuselage skin cracks adjacent to the skin lap joints on 
airplanes that had scribe lines; the analysis resulted in different 
inspection zones, thresholds and repetitive intervals, and airplane 
groupings. We are proposing this AD to prevent rapid decompression of 
the airplane due to fatigue cracks resulting from scribe lines on 
pressurized fuselage structure.

DATE: We must receive comments on this proposed AD by July 6, 2009.

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. You may review copies of the referenced 
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 or 425-227-
1152.

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 proposed 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: Wayne Lockett, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6447; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0452; 
Directorate Identifier 2007-NM-326-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed 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 proposed AD.

Discussion

    On March 20, 2006, we issued AD 2006-07-12, amendment 39-14539 (71 
FR 16211, March 31, 2006), for all Boeing Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes. That AD requires a one-time 
inspection for scribe lines and cracks in the fuselage skin at certain 
lap joints, butt joints, external repair doublers, and other areas; and 
related investigative/corrective actions if necessary. That AD resulted 
from reports of fuselage skin cracks adjacent to the skin lap joints on 
airplanes that had scribe lines. Scribe line damage can also occur at 
many other locations, including butt joints, external doublers, door 
scuff plates, the wing-to-body fairing, and areas of the fuselage where 
decals have been applied or removed. We issued that AD to prevent rapid 
decompression of the airplane due to fatigue cracks resulting from 
scribe lines on pressurized fuselage structure.

Related ADs

    This proposed AD is similar to AD 2007-19-07, amendment 39-15198 
(72 FR 60244, October 24, 2007), which applies to all Boeing Model 757-
200, -200PF, and -200CB series airplanes. That AD requires inspections 
to detect scribe lines in the fuselage skin at certain lap joints, butt 
joints, external repair doublers, and other areas; and related 
investigative/corrective actions if necessary. Those actions resulted 
from reports of fuselage skin cracks adjacent to the skin lap joints on 
airplanes that had scribe lines.

[[Page 23665]]

Actions Since Existing AD Was Issued

    AD 2006-07-12 cites Boeing Alert Service Bulletin 737-53A1262, 
dated December 9, 2004, as the appropriate source of service 
information for the scribe line inspection. Since we issued that AD, 
Boeing issued Alert Service Bulletin 737-53A1262, Revision 3, dated 
October 16, 2008. Revisions to the service bulletin were based on 
additional detailed analysis that indicated the need to inspect some 
affected areas of the skin. In addition, based on the additional 
analysis, the service bulletin establishes two new inspection zones, 
Zone 4 and Zone 5, with thresholds of 50,000 and 60,000 flight cycles, 
respectively, since first scribe opportunity. The revised service 
bulletin designated certain areas of fuselage skin into other 
inspection zones, and some of those areas might now require inspections 
earlier than required by the existing AD. These areas are to be 
inspected within 4,500 flight cycles from the effective date of the new 
AD or prior to the revised zonal threshold, whichever is later.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2006-07-12 and retain the requirements of the 
existing AD, require inspection of newly added Zones 4 and 5, reduce 
certain compliance thresholds, and require inspection results to be 
sent to Boeing.
    In addition, we have moved the content of paragraph (p)(4) of AD 
2006-07-12 (from its location under the ``Alternative Methods of 
Compliance'' heading) to new paragraph (w) in this NPRM. New paragraph 
(w) specifies that a repair plan approved by a Boeing Company 
Authorized Representative or Designated Engineering Representative is 
acceptable for compliance with certain repair requirements of the 
proposed AD (provided certain conditions have been met). The provisions 
in paragraph (w) are considered a different repair method--not an 
alternative method of compliance (AMOC), which can be issued only after 
an AD has been issued.

Differences Between Proposed AD and Service Bulletin

    Boeing Alert Service Bulletin 737-53A1262, Revision 3, dated 
October 16, 2008, specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
Organization whom we have authorized to make those findings.

Costs of Compliance

    There are about 2,685 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs, 
including the costs for the new proposed inspection areas in Zones 4 
and 5, for U.S. operators to comply with this proposed AD.

                                                        Estimated Costs Required by AD 2006-07-12
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          Number of U.S.-
                Zone                                Action                  Work hours     Average labor     Cost per       registered      Fleet cost
                                                                                           rate per hour     airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
1...................................  Sealant removal...................              66             $80          $5,280             787      $4,155,360
                                      Inspection........................               4              80             320             787         251,840
2...................................  Sealant removal...................              38              80           3,040             787       2,392,480
                                      Inspection........................              29              80           2,320             787       1,825,840
3...................................  Sealant removal...................              88              80           7,040             787       5,540,480
                                      Inspection........................              38              80           3,040             787       2,392,480
--------------------------------------------------------------------------------------------------------------------------------------------------------

                                                   Estimated Costs Required by New Actions of This AD
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          Number of U.S.-
                Zone                                Action                  Work hours     Average labor     Cost per       registered      Fleet cost
                                                                                           rate per hour     airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
4...................................  Sealant removal...................              15             $80          $1,200             787        $944,400
                                      Inspection........................               1              80              80             787          62,960
5...................................  Sealant removal...................              31              80           2,480             787       1,951,760
                                      Inspection........................               2              80             160             787         125,920
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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.

[[Page 23666]]

    For the reasons discussed above, I certify that the proposed 
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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14539 (71 FR 16211, March 31, 2006) and adding 
the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2009-0452; Directorate Identifier 2007-NM-
326-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 6, 
2009.

Affected ADs

    (b) This AD supersedes AD 2006-07-12.

Applicability

    (c) This AD applies to all Boeing Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes, certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from reports of fuselage skin cracks 
adjacent to the skin lap joints on airplanes that had scribe lines. 
Scribe line damage can also occur at many other locations, including 
butt joints, external doublers, door scuff plates, the wing-to-body 
fairing, and areas of the fuselage where decals have been applied or 
removed. We are issuing this AD to prevent rapid decompression of 
the airplane due to fatigue cracks resulting from scribe lines on 
pressurized fuselage structure.

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 2006-07-12

Inspection

    (g) Do a detailed inspection for scribe lines and cracks in the 
fuselage skin at certain lap joints, butt joints, external repair 
doublers, and other areas, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1262, dated 
December 9, 2004, except as provided by paragraphs (h), (k), (l), 
(m), (n), and (o) of this AD. Except as required by paragraph (q) of 
this AD, do the actions at the time specified in paragraph 1.E., 
``Compliance,'' of the service bulletin, except as required by 
paragraph (j) of this AD. Acceptable inspection exemptions are 
described in paragraph 1.E.1. of Boeing Alert Service Bulletin 737-
53A1262, dated December 9, 2004.
    (1) If no scribe line is found, no further work is required by 
this paragraph.
    (2) If any scribe line is found: Do all applicable investigative 
and corrective actions at the time specified in paragraph 1.E. of 
Boeing Alert Service Bulletin 737-53A1262, dated December 9, 2004, 
by doing all applicable actions specified in the service bulletin, 
except as required by paragraph (h) of this AD.

    Note 1: A detailed inspection is defined in Note 10 of Boeing 
Alert Service Bulletin 737-53A1262, dated December 9, 2004, under 
paragraph 3.A., ``General Information.'' Specific magnification 
requirements may be specified in the steps of the Work Instructions.

Exceptions to and Clarification of Service Bulletin 737-53A1262 
Procedures

    (h) Paragraph (g) of this AD requires accomplishment of Parts 1 
through 11 of Boeing Alert Service Bulletin 737-53A1262, dated 
December 9, 2004. Parts 12 and 13 of the service bulletin may be 
accomplished, if applicable, to allow temporary return to service. 
This AD does not require accomplishment of Part 14 of the service 
bulletin, although the FAA-approved procedures described in Part 14 
are acceptable for continued operation with scribe lines found 
before the applicable compliance time.
    (i) If any scribe line or crack is found during any inspection 
required by paragraph (g) of this AD, and Boeing Alert Service 
Bulletin 737-53A1262, dated December 9, 2004, specifies to contact 
Boeing for appropriate action: Before further flight, inspect or 
repair scribe lines and repair cracks using a method approved in 
accordance with the procedures specified in paragraph (x) of this 
AD.
    (j) Where Boeing Alert Service Bulletin 737-53A1262, dated 
December 9, 2004, specifies a compliance time after the issuance of 
the service bulletin, this AD requires compliance within the 
specified compliance time after May 5, 2006 (the effective date of 
AD 2006-07-12).
    (k) Certain figures are incorrectly identified in Boeing Alert 
Service Bulletin 737-53A1262, dated December 9, 2004. The figure 
cited in Part 8, step 3, should be Figure 39, not Figure 38. The 
figure cited in Part 9, step 4, should be Figure 38, not Figure 39.
    (l) If the operator's records show that the airplane has never 
been stripped and repainted under the dorsal fin fairing since 
delivery from Boeing, then this AD does not require inspections of 
the butt joint, lap joint, and repair, as specified in paragraph (g) 
of this AD, in the areas under the dorsal fin fairing.
    (m) Figure 37 of Boeing Alert Service Bulletin 737-53A1262, 
dated December 9, 2004, defines ``Restricted Zones'' at door cutouts 
as the only affected structure. Paragraph (g) of this AD considers 
this area to also include Zone 1B.
    (n) In Figure 1, sheets 2 and 3, of Boeing Service Bulletin 737-
53A1262, dated December 9, 2004, the first condition for the initial 
compliance threshold for Areas B, C, and E is for areas where the 
cutout modification shown in Boeing Service Bulletin 737-53A1177 was 
accomplished. Paragraph (g) of this AD considers this condition to 
also include Zone 1B.
    (o) In Figure 1, sheets 2 and 3, of Boeing Alert Service 
Bulletin 737-53A1262, dated December 9, 2004, the second condition 
for the initial compliance threshold for Areas B, C, and E is for 
areas where the cutout modification shown in Boeing Service Bulletin 
737-53A1177 was not accomplished. Paragraph (g) of this AD considers 
this condition to apply only to Zone 1A.

Reporting Requirement

    (p) For airplanes on which inspections have been done in 
accordance with Boeing Alert Service Bulletin 737-53A1262, dated 
December 9, 2004: At the applicable time specified in paragraph 
(p)(1) or (p)(2) of this AD, submit a report of positive findings of 
cracks found during the inspection required by paragraph (g) of this 
AD to the Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. Alternatively, operators may submit reports 
to their Boeing field service representatives. The report shall 
contain, as a minimum, the following information: airplane serial 
number, flight cycles at time of discovery, location(s) and extent 
of positive crack findings. Under the provisions of the Paperwork 
Reduction Act of 1980 (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 before May 5, 2006: Send the 
report within 30 days after May 5, 2006.
    (2) If the inspection was done after May 5, 2006: Send the 
report within 30 days after the inspection is done.

[[Page 23667]]

New Requirements of This AD

Inspection

    (q) As of the effective date of this AD, the actions for Zones 
1, 2, and 3, as specified in paragraph (g) of this AD, must be done 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1262, Revision 3, dated October 16, 2008, 
and at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Revision 3 of the service bulletin, except as 
specified in paragraph (s) of this AD.

    Note 2:  Paragraph 1.E.5. of Boeing Alert Service Bulletin 737-
53A1262, Revision 3, dated October 16, 2008, provides a grace period 
for airplanes that have exceeded the revised thresholds.

Inspection of Zones 4 and 5

    (r) Do a detailed inspection for scribe lines and cracks in 
Zones 4 and 5 (adjacent to lap joints on skin panels that do not 
have bonded doublers), as specified in Boeing Alert Service Bulletin 
737-53A1262, Revision 3, dated October 16, 2008. Except as provided 
by paragraph (s) of this AD, do the actions in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1262, Revision 3, dated October 16, 2008, and at the applicable 
time specified in paragraph 1.E., ``Compliance,'' of the service 
bulletin, or within 4,500 flight cycles after the effective date of 
this AD, whichever occurs later.
    (1) If no scribe line or crack is found: No further work is 
required by this paragraph.
    (2) If any scribe line or crack is found: Do all applicable 
investigative and corrective actions at the time specified in 
paragraph 1.E. of Boeing Alert Service Bulletin 737-53A1262, 
Revision 3, dated October 16, 2008, by doing all applicable actions 
specified in the Accomplishment Instructions of Boeing Alert Service 
Bulletin 737-53A1262, Revision 3, dated October 16, 2008, except as 
required by paragraph (s)(1) of this AD.

Exceptions to Specifications of Boeing Alert Service Bulletin 737-
53A1262, Revision 3, Dated October 16, 2008

    (s) The following exceptions to Boeing Alert Service Bulletin 
737-53A1262, Revision 3, dated October 16, 2008, apply to this AD:
    (1) If any scribe line or crack is found during any inspection 
required by this AD, and Boeing Alert Service Bulletin 737-53A1262, 
Revision 3, dated October 16, 2008, specifies to contact Boeing for 
appropriate action: Before further flight, inspect or repair scribe 
lines and repair cracks using a method approved in accordance with 
the procedures specified in paragraph (x) of this AD.
    (2) Where Boeing Alert Service Bulletin 737-53A1262, Revision 3, 
dated October 16, 2008, specifies a compliance time after the 
issuance of the service bulletin, this AD requires compliance within 
the specified compliance time after the effective date of this AD.
    (3) If the operator's records show that the airplane has never 
been stripped and repainted under the dorsal fin fairing since 
delivery from Boeing, then this AD does not require inspections of 
the butt joint, lap joint, and repair, as specified in paragraphs 
(g), (q), and (r) of this AD, in the areas under the dorsal fin 
fairing.
    (4) For airplanes in Groups 3 and 29, as identified in Boeing 
Alert Service Bulletin 737-53A1262, Revision 3, dated October 16, 
2008: At the applicable times specified in paragraphs (s)(4)(i), 
(s)(4)(ii), and (s)(4)(iii) of this AD, perform a detailed 
inspection for scribe lines and cracks on the main cargo door along 
the lower edge of the upper hinge, around external repairs, and 
around decals, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-53A1262, Revision 3, dated October 
16, 2008, or using a method approved in accordance with the 
procedures specified in paragraph (x) of this AD. If no scribe line 
or crack is found, no further work is required by this paragraph. If 
any scribe line or crack is found, do all applicable related 
investigative and corrective actions at the time specified in 
paragraph 1.E. of Boeing Alert Service Bulletin 737-53A1262, 
Revision 3, dated October 16, 2008, by doing all applicable actions 
specified in the Accomplishment Instructions of the service 
bulletin, except as required by paragraphs (s)(1), (s)(2), and 
(s)(3) of this AD.
    (i) For areas along the lower edge of the door hinge from BS 360 
to BS 500, the initial compliance threshold is to be determined 
using Zone 1B.
    (ii) For external repairs, the initial compliance threshold is 
to be determined using Zone 1B.
    (iii) For decals, the initial compliance threshold is to be 
determined using Zone 2.
    (5) For Group 11 airplanes, as specified in Boeing Alert Service 
Bulletin 737-53A1262, Revision 3, dated October 16, 2008: Stringer 
20R between BS 727C and BS 727D+10 is in Zone 1B.

Actions Accomplished in Accordance With Previous Service Information

    (t)(1) Actions accomplished before the effective date of this AD 
in accordance with Boeing Alert Service Bulletin 737-53A1262, dated 
December 9, 2004, are acceptable for compliance with the 
corresponding requirements of paragraph (q) of this AD.
    (2) Actions accomplished before the effective date of this AD in 
accordance with the Boeing Service Bulletin 737-53A1262, Revision 1, 
dated March 1, 2007; or Revision 2, dated September 20, 2007; are 
acceptable for compliance with the corresponding requirements of 
paragraphs (g), (q), and (r) of this AD.

Clarification of Procedures in the Service Bulletin

    (u) For airplanes on which inspections are done as of the 
effective date of this AD: This AD requires accomplishment of Parts 
1 through 11, 15, and 16 of Boeing Alert Service Bulletin 737-
53A1262, Revision 3, dated October 16, 2008. Parts 12 and 13 of 
Boeing Alert Service Bulletin 737-53A1262, Revision 3, dated October 
16, 2008, may be accomplished, if applicable, to allow temporary 
return to service. This AD does not require accomplishment of Part 
14 of Boeing Alert Service Bulletin 737-53A1262, Revision 3, dated 
October 16, 2008, although the FAA-approved procedures described in 
Part 14 are acceptable for continued operation with scribe lines 
found before the applicable compliance time.

Report

    (v) For airplanes on which inspections are done in accordance 
with the service information identified in Table 1 of this AD: At 
the applicable time specified in paragraph (v)(1) or (v)(2) of this 
AD, submit a report of positive findings of cracks found during the 
inspections required by paragraphs (q), (r), and (s)(4) of this AD 
to the Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. Alternatively, operators may submit reports 
to their Boeing field service representatives. The report must 
contain, as a minimum, the following information: airplane serial 
number, flight cycles at time of discovery, location(s) and extent 
of positive crack findings. 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) For an inspection done before the effective date of this AD: 
Send the report within 30 days after the effective date of this AD.
    (2) For an inspection done after the effective date of this AD: 
Send the report within 30 days after the inspection is done.

                                          Table 1--Service Information
----------------------------------------------------------------------------------------------------------------
          Boeing service information               Revision                           Date
----------------------------------------------------------------------------------------------------------------
Alert Service Bulletin 737-53A1262............               3  October 16, 2008.
Service Bulletin 737-53A1262..................               1  March 1, 2007.
Service Bulletin 737-53A1262..................               2  September 20, 2007.
----------------------------------------------------------------------------------------------------------------

[[Page 23668]]

Repair Plan In Lieu of Required Inspections

    (w) A repair plan approved by a Boeing Company Authorized 
Representative or Designated Engineering Representative before the 
effective date of this AD is acceptable for compliance with the 
requirements of paragraphs (g)(2), (i), (q), (r), (s)(1), and (s)(4) 
of this AD, provided the approval was documented via FAA Form 8110-3 
or 8100-9, and identified scribe line damage in the title of the 
form.

Alternative Methods of Compliance (AMOCs)

    (x)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19. Send information to ATTN: Wayne 
Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle 
Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 917-6447; fax (425) 917-6590.
    (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 an 
Authorized Representative (AR) for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the approval must meet the certification 
basis of the airplane, and the approval must specifically refer to 
this AD.

    Issued in Renton, WA, on May 6, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-11707 Filed 5-19-09; 8:45 am]

BILLING CODE 4910-13-P