[Federal Register Volume 78, Number 1 (Wednesday, January 2, 2013)]
[Rules and Regulations]
[Pages 9-15]
[FR Doc No: 2012-30924]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1419; Directorate Identifier 2010-NM-281-AD;
Amendment 39-17297; AD 2012-26-02]
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 an existing airworthiness directive (AD)
for certain The Boeing Company Model 737-300, -400, and -500 series
airplanes. That AD currently requires repetitive inspections for
cracking of the crown area of the fuselage skin, and corrective actions
if necessary. This new AD adds repetitive inspections for cracking
using different inspection methods and inspecting additional areas, and
corrective actions if necessary. This new AD also requires additional
repairs to previously repaired areas and repetitive inspections for
loose fasteners and replacement if necessary in certain previously
repaired areas. This AD also reduces certain compliance times and
extends certain other compliance times. This AD was prompted by
additional reports of

cracking at the horizontal chem-mill steps away from the lap joints
over the entire crown area, and vertical chem-mill cracks adjacent to
the butt joints. We are issuing this AD to detect and correct fatigue
cracking of the fuselage skin, which could cause the fuselage skin to
fracture and fail, and result in rapid decompression of the airplane.

DATES: This AD is effective February 6, 2013.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of February 6,
2013.
    The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of August
1, 2005 (70 FR 36821, June 27, 2005).

ADDRESSES: 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<PHONE_NUMBER>; 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<PHONE_NUMBER>.

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:<PHONE_NUMBER>) 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: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-
6447; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2005-13-27, Amendment 39-14164 (70 FR 36821,
June 27, 2005). That AD applies to the specified products. The NPRM
published in the Federal Register on January 19, 2012 (77 FR 2669).
That NPRM proposed to continue to require repetitive inspections for
cracking of the crown area of the fuselage skin, and corrective actions
if necessary. That NPRM also proposed to add repetitive inspections for
cracking using different inspection methods and would inspect
additional areas, and corrective actions if necessary. That NPRM also
proposed to require additional repairs to previously repaired areas and
repetitive inspections for loose fasteners and replacement if necessary
in certain previously repaired areas. That NPRM also proposed to reduce
certain compliance times and extend certain other compliance times.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 2669, January 19, 2012) and the FAA's response to each comment.

Concurrence With NPRM (77 FR 2669, January 19, 2012)

    The National Transportation Safety Board stated that it fully
supports the NPRM (77 FR 2669, January 19, 2012).

Request To Correct References to Repair Instructions

    Boeing asked that we revise the NPRM (77 FR 2669, January 19, 2012)
to correct references to certain repair instructions. Boeing stated
that paragraph (n)(2)(iii) of the NPRM specifies converting the time-
limited repair into a permanent repair by doing the permanent repair
specified in paragraph (n)(1) of the NPRM. Boeing noted that paragraph
(n)(1) of the NPRM specifies installing a permanent repair in
accordance with ``Part 2'' of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1234, Revision 2, dated November 24,
2010; however, Part 2 does not give instructions for changing the time-
limited repair to a permanent repair. Boeing stated that paragraph
(t)(2) of the NPRM also incorrectly refers to converting the time-
limited repair into a permanent repair by doing the permanent repair
specified in paragraph (n)(1) of the NPRM.
    Boeing stated that the correct instructions for converting the
time-limited repair to a permanent repair are specified in Part 4 of
the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1234, Revision 2, dated November 24, 2010, and added that paragraphs
(n)(2)(iii) and (t)(2) of the NPRM (77 FR 2669, January 19, 2012)
should specify doing the permanent repair in accordance with Part 4 of
the Accomplishment Instructions of that service information.
    We agree that the reference to paragraph (n)(1) of this AD for
doing the permanent repair identified in paragraphs (n)(2)(iii) and
(t)(2) of this AD is incorrect. We have changed paragraph (n)(2)(iii)
of this AD to specify doing the permanent repair in accordance with
Part 4 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1234, Revision 2, dated November 24, 2010. In addition,
we have changed paragraph (t)(2) of this AD to refer to paragraph
(t)(3) of this AD for the permanent repair. Paragraph (t)(3) of this AD
specifies doing the permanent repair in accordance with paragraph
3.B.4. (i.e., Part 4) of the service information.

Request To Remove Certain Terminating Action

    Boeing asked that we delete the last sentence in paragraph (t)(1)
of the NPRM (77 FR 2669, January 19, 2012), which specified that
installation of internal tear strap doublers would terminate the
inspections required by paragraph (m) of the NPRM. Boeing stated that
this sentence is not necessary because there are no inspection
requirements in paragraph (m) of the NPRM for the areas covered by
permanent repairs installed without tear strap doublers.
    We agree with the commenter for the reason provided. We have
deleted the referenced sentence in paragraph (t)(1) of this AD.

Request To Add Certain Terminating Action Language

    Southwest Airlines (SWA) asked that we add language to paragraphs
(n) and (s) of the NPRM (77 FR 2669, January 19, 2012), specifying that
repairs installed in accordance with paragraphs (n) and (s) of the NPRM
terminate the inspections required by paragraphs (m), (o), (p), and (q)
of the NPRM.
    We partially agree with the commenter's request. The repetitive
inspections may be terminated after a time-limited or permanent repair
has been installed, for the repaired area only. We note that paragraph
(n) of this AD specifies that doing a permanent repair terminates the
inspections specified in paragraph (m) of this AD for the repaired area
only. We also note that paragraph (n) of this AD does not terminate
paragraphs (o), (p), and (q) of this AD. Accomplishing paragraph (s) of
this AD terminates the inspections

required by paragraphs (o), (p), and (q) of this AD. We have changed
paragraph (s) of this AD accordingly.

Request To Include Additional Service Information

    SWA asked that we include the internal inspection procedure
specified in Boeing 737 Nondestructive Test (NDT) Manual, Part 6,
Chapter 53-30-20, as an acceptable method for accomplishing the
inspections in areas covered by non-terminating repairs as required by
paragraphs (m), (o), (p), and (q) of the NPRM (77 FR 2669, January 19,
2012). SWA stated that the inspection procedure in the NDT manual has
been previously approved as an alternative inspection method for
paragraph (s) of AD 2005-13-27, Amendment 39-14164 (70 FR 36821, June
27, 2005), in areas covered by an existing repair that do not meet the
terminating repair specified in the compliance tables in Boeing Alert
Service Bulletin 737-53A1234, Revision 2, dated November 24, 2010.
    We disagree with the commenter's request. Operators may submit a
request for approval of an alternative method of compliance (AMOC) to
use the inspection procedure specified in the NDT manual for
accomplishing the inspections in areas covered by non-terminating
repairs, as specified in paragraph (x) of this AD. We have not changed
this AD in this regard.

Request To Change Compliance Time

    SWA asked that we change the compliance time for the inspections
proposed by paragraphs (g), (m), (o), (p), and (q) of the NPRM (77 FR
2669, January 19, 2012) from ``total flight cycles'' to ``flight cycles
since panel replacement'' for airplanes on which fuselage crown skin
panels that were replaced in accordance with Boeing Service Bulletin
737-53-1306, dated September 22, 2010; Revision 1, dated March 17,
2011; or Revision 2, dated October 25, 2011. SWA stated that this
modification replaces crown skin panels with new skin panels, and the
new skin panels should have a threshold ``from panel replacement,'' and
not ``total airplane cycles.'' SWA added that accomplishing Boeing
Service Bulletin 737-53-1306, original issue, Revision 1, or Revision 2
has been approved previously as an AMOC to certain requirements in
multiple ADs; including AD 2005-13-27, Amendment 39-14164 (70 FR 36821,
June 27, 2005), which is being superseded by the NPRM. SWA stated that
the AMOC provides approval for changes in compliance time from total
flight cycles to cycles since panel replacement.
    We do not agree with the commenter's request to change paragraphs
(g), (m), (o), (p), and (q) of this AD. The existing AMOC discussed by
the commenter is approved for the restated requirements of this AD,
including paragraph (g) of this AD. Due to the extent of the
replacement specified in Boeing Service Bulletin 737-53-1306, dated
September 22, 2010; Revision 1, dated March 17, 2011; or Revision 2,
dated October 25, 2011, and the number of ADs that affect that
replacement, we have determined that clarification of the AMOCs for all
these ADs should be provided in a separate AMOC letter. This will
ensure that multiple parties (e.g., Flight Standards, Maintenance
Repair and Overhaul facilities (MROs), and operators) have access to
the approval information for the replacement in one document. We have
made no change to this AD in this regard.

Request for Alternate Option for Inspections

    SWA asked that we revise the NPRM (77 FR 2669, January 19, 2012) to
allow the inspections in paragraph (w) of the NPRM as an alternate
option for the permanent repairs required by paragraph (t) of the NPRM
for airplanes on which internal tear strap doublers were not installed.
SWA stated that permanent repairs installed in accordance with Boeing
Special Attention Service Bulletin 737-53-1234, dated June 13, 2001; or
Revision 1, dated March 31, 2005; have been evaluated and determined to
meet the damage tolerance requirements of part 26 of the Federal
Aviation Regulations (14 CFR Part 26), as indicated in Figure 41 of
Boeing Alert Service Bulletin 737-53A1234, Revision 2, dated November
24, 2010. SWA added that accomplishing the post-repair inspections in
accordance with Figure 41, at the time specified in Table 7 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-
53A1234, Revision 2, dated November 24, 2010, should be considered an
alternate option to the requirements in paragraph (t) of the NPRM.
    We do not agree with the commenter's request. The 60,000-flight-
cycle threshold for the post-repair inspection addresses the critical
outer fastener row installed with the repair doubler, and does not
address the area of the tear strap doubler installed in accordance with
paragraph (t)(1) of this AD. We have made no change to this AD in this
regard.

Request To Provide Clarification

    SWA asked that we provide clarification whether the notes in
paragraph 3.B. of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1234, Revision 2, dated November 24, 2010, are
applicable to paragraphs (m), (o), (p), and (q) of the NPRM (77 FR
2669, January 19, 2012).
    We agree to provide clarification. The notes specified in paragraph
3.A., ``General Information,'' and paragraph 3.B., ``Work
Instructions,'' of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1234, Revision 2, dated November 24, 2010,
apply to all the sub-paragraphs of the Accomplishment Instructions,
including the actions that correspond to the requirements of paragraphs
(m), (o), (p), and (q) of this AD. We have made no change to this AD in
this regard.

Explanation of Change to This AD

    We have revised the heading for and the wording in paragraph (l) of
this AD; this change has not changed the intent of that paragraph.

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 2669, January 19, 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 2669, January 19, 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 109 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
               Action                      Labor cost          Cost per product       Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained actions from    94 work-hours x $85    $7,990 per inspection  $870,910
 AD 2005-13-27, Amendment             per hour = $7,990.     cycle.
 39[dash]14164 (70 FR 36821, June
 27, 2005)).
New NDI (non-destructive             Up to 390 work-hours   Up to $33,150 per      Up to $3,613,350.
 inspection) Inspections (medium      x $85 per hour =       inspection cycle.
 frequency eddy current, magneto      $33,150.
 optical imaging, C-scan, or
 ultrasonic phased array).
Install internal tear strap          Up to 30               Up to $2,550.........  Up to $277,950.
 doublers (for airplanes on which     work[dash]hours x
 permanent repair was already done).  $85 per hour =
                                      $2,550.
Inspection for loose fasteners (for  1 work-hour x $85 per  $85..................  $9,265.
 airplanes on which temporary         hour = $85.
 repair was already done)[sup1].
Install permanent repair (for        Up to 48               Up to $4,080.........  Up to $444,720.
 airplanes on which temporary         work[dash]hours x
 repair was already done)[sup1].      $85 per hour =
                                      $4,080.
Inspection adjacent to lap joint     3 work-hours x $85     $255.................  $27,795.
 repair[sup1].                        per hour = $255.
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\1\ The cost for this action is for one typical repair only.

    We estimate the following costs to do any necessary repairs that
would be required based on the results of the inspection. We have no
way of determining the number of aircraft that might need these
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Repair \1\..........................  209 work-hours x $85     None...................  $17,765.
                                       per hour = $17,765.
----------------------------------------------------------------------------------------------------------------
\1\ Repair cost estimate is for one typical repair only.

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)
2005-13-27, Amendment 39-14164 (70 FR 36821, June 27, 2005), and adding
the following new AD:

2012-26-02 The Boeing Company: Amendment 39-17297; Docket No. FAA-
2011-1419; Directorate Identifier 2010-NM-281-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective February 6, 2013.

(b) Affected ADs

    This AD supersedes AD 2005-13-27, Amendment 39-14164 (70 FR
36821, June 27, 2005).

(c) Applicability

    This AD applies to The Boeing Company Model 737-300, -400, and -
500 series airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin 737-53A1234, Revision 2, dated
November 24, 2010.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracking at the horizontal
chem-mill steps away from the lap joints over the entire crown area,
and vertical chem-mill cracks adjacent to the butt joints. We are
issuing this AD to detect and correct fatigue cracking of the
fuselage skin, which could cause the fuselage skin to fracture and
fail, and result in rapid decompression of the airplane.

(f) Compliance

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

(g) Retained Initial Inspections

    This paragraph restates the requirements of paragraph (g) of AD
2005-13-27, Amendment 39-14164 (70 FR 36821, June 27, 2005). At the
later of the times specified in paragraphs (g)(1) and (g)(2) of this
AD, perform detailed and eddy current inspections for cracking of
the crown area of the fuselage skin in accordance with Part 1,
including the ``Note,'' of the Work Instructions of Boeing Special
Attention Service Bulletin 737-53-1234, Revision 1, dated March 31,
2005, except as provided by paragraph (j) of this AD. Doing the
inspections required by paragraph (m) of this AD terminates the
inspections required by this paragraph for the corresponding
inspection areas.
    (1) Before the accumulation of the applicable total flight
cycles specified in the ``Threshold'' column of Table 1 of Figure 1
of Boeing Special Attention Service Bulletin 737-53-1234, Revision
1, dated March 31, 2005.
    (2) Within 4,500 flight cycles after August 1, 2005 (the
effective date of AD 2005-13-27, Amendment 39-14164 (70 FR 36821,
June 27, 2005).

(h) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (h) of AD
2005-13-27, Amendment 39-14164 (70 FR 36821, June 27, 2005). Repeat
either the detailed or eddy current inspections specified in
paragraph (g) of this AD at the applicable intervals specified in
paragraph (h)(1) or (h)(2) of this AD until paragraph (i)(1) or
(i)(2) of this AD has been done, as applicable. Doing the inspection
required by paragraph (m) of this AD terminates the inspections
required by this paragraph for the corresponding inspection area.
    (1) Repeat the detailed inspections thereafter at intervals not
to exceed 1,200 flight cycles.
    (2) Repeat the eddy current inspections thereafter at intervals
not to exceed 3,000 flight cycles.

(i) Retained Permanent or Time-Limited Repair for Cracking Found During
Inspections

    This paragraph restates the requirements of paragraph (i) of AD
2005-13-27, Amendment 39-14164 (70 FR 36821, June 27, 2005). If any
cracking is found during any inspection required by paragraph (g) or
(h) of this AD, do the actions specified in paragraph (i)(1) or
(i)(2) of this AD, in accordance with Boeing Special Attention
Service Bulletin 737-53-1234, Revision 1, dated March 31, 2005,
except as provided by paragraphs (j) and (k) of this AD.
    (1) Before further flight, do a permanent repair (including
related investigative actions and applicable corrective actions) in
accordance with Part 2 of the Work Instructions of Boeing Special
Attention Service Bulletin 737-53-1234, Revision 1, dated March 31,
2005. Doing a permanent repair ends the repetitive inspections
required by paragraph (h) of this AD for the repaired area only.
    (2) Do the actions specified in paragraphs (i)(2)(i) and
(i)(2)(ii) of this AD at the time specified in the applicable
paragraph. Doing a time-limited repair ends the repetitive
inspections required by paragraph (h) of this AD for the repaired
area only.
    (i) Before further flight, do a time-limited repair (including
related investigative actions and applicable corrective actions) in
accordance with Part 3 of the Work Instructions of Boeing Special
Attention Service Bulletin 737-53-1234, Revision 1, dated March 31,
2005.
    (ii) At the times specified in Figure 8 of Boeing Special
Attention Service Bulletin 737-53-1234, Revision 1, dated March 31,
2005, do the related investigative and corrective actions in
accordance with Part 3 of the Work Instructions of Boeing Special
Attention Service Bulletin 737-53-1234, Revision 1, dated March 31,
2005.

(j) Retained Provision for Repair per FAA

    This paragraph restates the requirements of paragraph (j) of AD
2005-13-27, Amendment 39-14164 (70 FR 36821, June 27, 2005). Where
Boeing Special Attention Service Bulletin 737-53-1234, Revision 1,
dated March 31, 2005, specifies to contact Boeing for appropriate
action: Before further flight, repair according to a method approved
by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or
according to data meeting the certification basis of the airplane
approved by an Authorized Representative for the Boeing Delegation
Option Authorization Organization who has been authorized by the
Manager, Seattle ACO, to make those findings; or using a method
approved in accordance with the procedures specified in paragraph
(x) of this AD. For a repair method to be approved, the approval
must specifically reference this AD.

(k) Retained Provision, Reporting Not Required

    This paragraph restates the provisions of paragraph (k) of AD
2005-13-27, Amendment 39-14164 (70 FR 36821, June 27, 2005).
Although Boeing Special Attention Service Bulletin 737-53-1234,
Revision 1, dated March 31, 2005, specifies reporting certain
information to Boeing, this AD does not require that action.

(l) Retained Credit for Previous Actions

    This paragraph restates the requirements of paragraph (l) of AD
2005-13-27, Amendment 39-14164 (70 FR 36821, June 27, 2005). Actions
done before August 1, 2005, in accordance with Boeing Special
Attention Service Bulletin 737-53-1234, dated June 13, 2002 (which
is not incorporated by reference in this AD), are acceptable for
compliance with the corresponding actions required by paragraphs
(g), (h), and (i) of this AD.

(m) New Fuselage Skin Inspections at Chem-Mill Steps Common to Lap
Joints

    Except as provided by paragraph (v)(1) of this AD, at the
applicable time specified in Tables 1 and 2 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1234,
Revision 2, dated November 24, 2010: Do a non-destructive inspection
(NDI) (medium frequency eddy current, magneto optical imaging, C-
scan, or ultrasonic phased array) for horizontal chem-mill cracking
above the S-4 and S-10 lap joints, in accordance with paragraph
3.B.1.a. of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1234, Revision 2, dated November 24, 2010, except as
provided by paragraph (r) of this AD. Repeat the applicable
inspections thereafter at intervals not to exceed those specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1234, Revision 2, dated November 24, 2010. Accomplishment of
the inspections required by this paragraph terminates the
requirements of paragraphs (g) and (h) of this AD for the
corresponding inspection areas.

    Note 1 to paragraph (m) of this AD:
     Option 1 of Boeing Alert Service Bulletin 737-53A1234, Revision
2, dated November 24, 2010, specifies doing one of the following
NDI: Medium frequency eddy current inspection, magneto optical
imaging inspection, or C-scan inspection. Option 2 specifies doing
one NDI--an external ultrasonic phased array inspection. These
options have different compliance times after the initial
inspection.

(n) New Permanent or Time-Limited Repair for Cracking Found During
Inspections Required by Paragraph (m) of This AD

    If any cracking is found during any inspection required by
paragraph (m) of this AD, do the actions specified in paragraph
(n)(1) or (n)(2) of this AD.
    (1) Before further flight, do a permanent repair, including
related investigative actions and applicable corrective actions, in
accordance with Part 2 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1234, Revision 2, dated November 24,
2010, except as provided by paragraph (v)(2) of this AD. Doing a
permanent repair ends the repetitive inspections required by
paragraph (m) of this AD for the repaired area only.
    (2) Do the actions specified in paragraphs (n)(2)(i),
(n)(2)(ii), and (n)(2)(iii) of this AD at the time specified in the
applicable paragraph. Doing a time-limited repair ends the
repetitive inspections required by paragraph (m) of this AD for the
repaired area only.
    (i) Before further flight, do a time-limited repair, including
related investigative actions and applicable corrective actions, in
accordance with Part 4 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1234, Revision 2, dated November 24,
2010, except as provided by paragraph (v)(2) of this AD.
    (ii) Within 3,000 flight cycles after the time-limited repair
was installed as specified in paragraph (n)(2)(i) of this AD, or
within 500 flight cycles after the effective date of this AD,
whichever occurs later, do a detailed inspection for loose
fasteners, in accordance with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1234, Revision
2, dated November 24, 2010. Repeat the inspection thereafter at
intervals not to exceed 3,000 flight cycles until the permanent
repair required by paragraph (n)(2)(iii) of this AD is done. If any
loose fasteners are found, before further flight, replace the
fasteners with new fasteners of the same type and size, as specified
in Figures 6, 35, and 36 of Boeing

Alert Service Bulletin 737-53A1234, Revision 2, dated November 24,
2010.
    (iii) Within 6,000 flight cycles after the time-limited repair
was installed, as specified in paragraph (n)(2)(i) of this AD, do
the permanent repair, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1234, Revision 2, dated November 24, 2010, except as provided by
paragraph (v)(2) of this AD.

(o) New Fuselage Skin Inspections at Chem-Mill Steps Common to Shear
Wrinkle Areas

    Except as provided by paragraph (v)(1) of this AD, at the
applicable time specified in Table 3 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1234,
Revision 2, dated November 24, 2010: Do an NDI (medium frequency
eddy current, magneto optical imaging, C-scan, or ultrasonic phased
array) for horizontal chem-mill cracking in the shear wrinkle areas,
in accordance with paragraph 3.B.1.b of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1234, Revision
2, dated November 24, 2010. Repeat the applicable inspections
thereafter at intervals not to exceed those specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1234,
Revision 2, dated November 24, 2010.

(p) New Fuselage Skin Inspections at Specified Vertical Chem-Mill Step
Locations

    Except as provided by paragraph (v)(1) of this AD, at the
applicable time specified in Table 4 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1234,
Revision 2, dated November 24, 2010: Do an NDI (medium frequency
eddy current, magneto optical imaging, C-scan, or ultrasonic phased
array) for vertical chem-mill cracking at locations specified in,
and in accordance with paragraph 3.B.1.c. of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1234, Revision
2, dated November 24, 2010. Repeat the applicable inspections
thereafter at intervals not to exceed those specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1234,
Revision 2, dated November 24, 2010.

(q) New Fuselage Skin Inspections at Chem-Mill Steps in General Pocket-
to-Pocket Areas

    Except as provided by paragraph (v)(1) of this AD, at the
applicable time specified in Tables 5 and 6 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1234,
Revision 2, dated November 24, 2010: Do an NDI (medium frequency
eddy current, magneto optical imaging, C-scan, or ultrasonic phased
array) for horizontal chem-mill cracking in general pocket-to-pocket
areas at specified locations in and in accordance with paragraphs
3.B.1.d., 3.B.1.e., and 3.B.1.f., as applicable, of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1234, Revision 2, dated November 24, 2010. Repeat the applicable
inspections thereafter at intervals not to exceed those specified in
Tables 5 and 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1234, Revision 2, dated November 24, 2010.

(r) New Inspection Exception

    For inspections required by paragraph (m) of this AD: It is not
necessary to inspect the chem-mill steps under an existing repair
installed using Boeing Special Attention Service Bulletin 737-53-
1234, dated June 13, 2002 (which is not incorporated by reference in
this AD); or Revision 1, dated March 31, 2005.

(s) New Repair of Cracking Found During Inspections Required by
Paragraphs (o) Through (q) of This AD

    If any crack is found during any inspection required by
paragraph (o), (p), or (q) of this AD, before further flight, repair
the crack using a method approved in accordance with the procedures
specified in paragraph (x) of this AD. Doing this repair ends the
repetitive inspections required by paragraphs (o), (p), and (q) of
this AD for the repaired area only.

(t) New Actions for Airplanes on Which Repairs Have Been Done Using
Previous Service Information

    (1) For airplanes on which permanent repairs have been done as
specified in Boeing Special Attention Service Bulletin 737-53-1234,
dated June 13, 2002 (which is not incorporated by reference in this
AD); or Revision 1, dated March 31, 2005; except airplanes on which
internal tear strap doublers were previously installed using a
repair plan approved using the procedures specified in paragraph (x)
of this AD: Within 6,000 flight cycles after the effective date of
this AD, install internal tear strap doublers, in accordance with
paragraph 3.B.3. of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1234, Revision 2, dated November 24, 2010,
except as provided by paragraph (v)(2) of this AD.
    (2) For airplanes on which time-limited repairs have been
installed as specified in Boeing Special Attention Service Bulletin
737-53-1234, dated June 13, 2002 (which is not incorporated by
reference in this AD); or Revision 1, dated March 31, 2005; except
airplanes on which the permanent repair has been installed before
the effective date of this AD as specified in Boeing Special
Attention Service Bulletin 737-53-1234, dated June 13, 2002 (which
is not incorporated by reference in this AD); or Revision 1, dated
March 31, 2005: Within 3,000 flight cycles after the time limited
repair is installed, or within 500 flight cycles after the effective
date of the AD, whichever occurs later, do a detailed inspection for
loose fasteners, in accordance with paragraph 3.B.4. of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1234, Revision 2, dated November 24, 2010. Repeat the inspection
thereafter at intervals not to exceed 3,000 flight cycles until the
permanent repair is installed in accordance with paragraph (t)(3) of
this AD. If any loose fasteners are found, before further flight,
replace the fasteners with new fasteners of the same type and size,
as specified in Figures 6, 35, and 36, as applicable, of Boeing
Alert Service Bulletin 737-53A1234, Revision 2, dated November 24,
2010.
    (3) For airplanes on which time-limited repairs have been
installed as specified in Boeing Special Attention Service Bulletin
737-53-1234, dated June 13, 2002 (which is not incorporated by
reference in this AD); or Revision 1, dated March 31, 2005; except
airplanes on which the permanent repair has been installed before
the effective date of this AD as specified in Boeing Special
Attention Service Bulletin 737-53-1234, dated June 13, 2002, or
Revision 1, dated March 31, 2005; before the effective date of this
AD: Within 6,000 flight cycles after the time-limited repair is
installed, or within 1,000 flight cycles after the effective date of
this AD, whichever occurs later, make the repair permanent by
replacing the blind fasteners in the time-limited repair with solid
rivets, and install internal tear strap doublers, in accordance with
paragraph 3.B.4. of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1234, Revision 2, dated November 24, 2010,
except as provided by paragraph (v)(2) of this AD.

(u) New Action Not in Accomplishment Instructions of Service
Information

    If any crack is found after the time-limited or permanent repair
is installed, and Boeing Alert Service Bulletin 737-53A1234,
Revision 2, dated November 24, 2010, specifies to contact Boeing for
appropriate action: Before further flight, repair the crack using a
method approved in accordance with the procedures specified in
paragraph (x) of this AD.

(v) Exceptions to Boeing Alert Service Bulletin 737-53A1234, Revision
2, Dated November 24, 2010

    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1234, Revision 2, dated November 24, 2010,
specifies a compliance time relative to the ``release of Revision 2
of this service bulletin,'' this AD requires compliance within the
specified compliance time after the effective date of this AD.
    (2) Where Boeing Alert Service Bulletin 737-53A1234, Revision 2,
dated November 24, 2010, specifies to contact Boeing for appropriate
action: Before further flight, repair the cracking using a method
approved in accordance with the procedures specified in paragraph
(x) of this AD.
    (3) Although Boeing Alert Service Bulletin 737-53A1234, Revision
2, dated November 24, 2010, specifies reporting certain information
to Boeing, this AD does not require that action.

(w) Post-Repair Inspections Not Required

    The post-repair inspection specified in Table 7 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1234,
Revision 2, dated November 24, 2010, is not required by this AD.

    Note 2 to paragraph (w) of this AD:
    The damage tolerance inspections specified in Table 7 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1234, Revision 2, dated November 24, 2010, may be used in
support of compliance with section 121.1109(c)(2) or 129.109(c)(2)
of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR
129.109(c)(2)). The corresponding actions specified in the
Accomplishment Instructions and Figures 40 and 41 of Boeing Alert
Service Bulletin 737-53A1234,

Revision 2, dated November 24, 2010, are not required in this AD.

(x) 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 attention of the person identified in the
Related Information section of this AD. Information may be emailed
to<EMAIL_ADDRESS>    (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 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 2005-13-27,
Amendment 39-14164 (70 FR 36821, June 27, 2005), are approved as
AMOCs for the corresponding requirements in this AD.

(y) Related Information

    (1) For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>    (2) 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<PHONE_NUMBER>; 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<PHONE_NUMBER>.

(z) 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 on February
6, 2013.
    (i) Boeing Alert Service Bulletin 737-53A1234, Revision 2, dated
November 24, 2010.
    (ii) Reserved.
    (4) The following service information was approved for IBR on
August 1, 2005 (70 FR 36821, June 27, 2005).
    (i) Boeing Special Attention Service Bulletin 737-53-1234,
Revision 1, dated March 31, 2005.
    (ii) Reserved.
    (5) 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<PHONE_NUMBER>; Internet https://www.myboeingfleet.com.
    (6) 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<PHONE_NUMBER>.
    (7) 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<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 12, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-30924 Filed 12-31-12; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register: May 15, 2009 (Volume 74, Number 93)]
[Notices]
[Page 22915]
[DOCID:fr15my09-51]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 13350-000]

Marine Power & Water, Inc.; Notice of Preliminary Permit
Application Accepted for Filing and Soliciting Comments, Motions To
Intervene, and Competing Applications

May 7, 2009.
    On January 6, 2009, Marine Power & Water, Inc. filed an
application, pursuant to section 4(f) of the Federal Power Act,
proposing to study the feasibility of the Colorado River Indian Tribes
Irrigation District Hydrokinetic Power Project, located in La Paz
County, Arizona. The sole purpose of a preliminary permit, if issued,
is to grant the permit holder priority to file a license application
during the permit term. A preliminary permit does not authorize the
permit holder to perform any land disturbing activities or otherwise
enter upon lands or waters owned by others without the owners' express
permission.
    The proposed project would be located in an irrigation canal
downstream from the Parker Irrigation Diversion Dam on the Colorado
River, within the Colorado River Indian Tribe Reservation, 3 miles
southwest of the City of Parker, Arizona, and would consist of: (1) One
hydrokinetic electrical generating unit, with a total installed
capacity of 15 kilowatts, (2) an existing 200-volt primary transmission
line at check 19 that interconnects with the Western Area Power
Administration, and (3) appurtenant facilities. The electricity
generated from the project would be used by the Colorado River Indian
Tribe Reservation. The project uses no dam or impoundment.
    Applicant Contact: Mr. Ray F. Hofmann, Marine Power & Water, Inc.,
26893 Calle Hermosa, Capistrano Beach, California 92624, phone: (949)
481-8331.
    FERC Contact: Carolyn Templeton<PHONE_NUMBER>.
    Deadline for filing comments, motions to intervene, competing
applications (without notices of intent), or notices of intent to file
competing applications: 60 days from the issuance of this notice.
Comments, motions to intervene, notices of intent, and competing
applications may be filed electronically via the Internet. See 18 CFR
385.2001(a)(1)(iii) and the instructions on the Commission's Web site
under the ``e-Filing'' link. If unable to be filed electronically,
documents may be paper-filed. To paper-file, an original and eight
copies should be mailed to: Kimberly D. Bose, Secretary, Federal Energy
Regulatory Commission, 888 First Street, NE., Washington, DC 20426. For
more information on how to submit these types of filings please go to
the Commission's Web site located at http://www.ferc.gov/filing-
comments.asp. More information about this project can be viewed or
printed on the ``eLibrary'' link of the Commission's Web site at http:/
/www.ferc.gov/docs-filing/elibrary.asp. Enter the docket number (P-
13350) in the docket number field to access the document. For
assistance, call toll-free 1-866-208-3372.

Kimberly D. Bose,
Secretary.
[FR Doc. E9-11334 Filed 5-14-09; 8:45 am]

BILLING CODE 6717-01-P


March 31, 2004 Ms. Kay Prince US Environmental Protection Agency Region 4 61 Forsyth St. S. W. Atlanta, GA 30303 8960 Dear Ms. Prince:

Please find enclosed the Unifour Area's Early Action Plan and the selected Emission Reduction Strategies. This fulfills the March 31, 2004 Unifour Early Action Compact milestone requirement.

We look forward to continuing work with the US EPA and the NC Division of Air Quality in efforts to help reduce pollution in the air that we breathe. Thank you for all the support you provide us in our efforts to make these goals successful. If you have any questions, or if we can provide any additional information please feel free to contact me at 828 322 9191 ext. 283.

Sincerely,

Judy G. McGuire WPCOG Air Quality Planner Cc: Richard Schutt, USEPA Sheila Holman, NCDAQ Unifour Air Quality Committee