[Federal Register Volume 78, Number 151 (Tuesday, August 6, 2013)]
[Rules and Regulations]
[Pages 47549-47555]
[FR Doc No: 2013-18765]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1156; Directorate Identifier 2011-NM-205-AD;
Amendment 39-17500; AD 2013-13-12]
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 airworthiness directive (AD) 2000-06-13 R1,
which applied to certain The Boeing Company Model 737-200, -200C, -300,
and -400 series airplanes. AD 2000-06-13 R1 required repetitively
inspecting for cracking of the corners of the door frame and the cross
beams of the aft cargo door, and corrective actions if necessary. AD
2000-06-13 R1 also required modifying the aft cargo door, which
terminates the repetitive inspections. This new AD adds airplanes to
the applicability, adds inspections and related investigative and
corrective actions, revises certain inspection types, and reduces a
certain compliance time for modifying the doors. This AD was prompted
by reports of cracking in the forward and aft corner frames of the aft
cargo door and in the lower cross beam. We are issuing this AD to
prevent fatigue cracking of the corners of the door frame and the cross
beams of the aft cargo door, which could result in rapid
depressurization of the airplane.

DATES: This AD is effective September 10, 2013.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of September 10,
2013.
    The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of May 9,
2000 (65 FR 17583, April 4, 2000).
    The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
December 24, 1998 (63 FR 67769, December 9, 1998).

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<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 98057-3356. 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: Alan Pohl, 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>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146,
July 11, 2001), which revised AD 2000-06-13, Amendment 39-11654 (65 FR
17583, April 4, 2000). AD 2000-06-13 superseded AD 98-25-06, Amendment
39-10931 (63 FR 67769, December 9, 1998). AD 2000-06-13 R1 applied to
the specified products. The NPRM published in the Federal Register on
December 4, 2012 (77 FR 71723). The NPRM proposed to continue to
require repetitively inspecting for cracking of the corners of the door
frame and the cross beams of the aft cargo door; doing corrective
actions if necessary; and modifying the aft cargo door, which
terminates the repetitive inspections. The NPRM also proposed to add
airplanes to the applicability, add inspections and related
investigative and corrective actions, revise certain inspection types,
and reduce a certain compliance time for modifying the doors.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 71723, December 4, 2012) and the FAA's response to each comment.

Request To Revise Compliance Time

    Boeing requested that we revise paragraph (o) of the NPRM (77 FR
71723, December 4, 2012), which specified the compliance time by
referring to paragraph 1.E. of Boeing Alert Service Bulletin 737-
52A1153, dated July 13, 2011. Boeing requested that we change this
compliance time to ``4,500 door flight cycles after the effective date
of this AD'' to avoid a potential conflict with other compliance times
in the NPRM. Boeing explained a scenario in which an operator could
comply with paragraph (o) of the NPRM within the required compliance
time, but then be immediately out of compliance with the proposed
inspection in paragraphs (p) and (q) of the NPRM.
    We partially agree with the request. As written, the compliance
time in paragraph (o) of the NPRM (77 FR 71723, December 4, 2012) could
result in a compliance conflict with other requirements of this AD for
doors subject to Boeing Alert Service Bulletin 737-52A1079, Revision 7,
dated December 17, 2010. We disagree, however, with Boeing's requested
compliance time, which would be unnecessarily more restrictive on
operators. Also, the referenced doors that have accumulated fewer than
27,000 total flight cycles should be provided the same compliance time
as doors subject to Boeing Alert Service Bulletin 737-52A1153, dated
July 13, 2011. We have therefore revised paragraphs (p) and (q) in this
final rule to change the compliance time to a threshold of 27,000 total
flight cycles on the door, with a grace period of 4,500 flight cycles.
Since paragraph (u)(4) of the NPRM is therefore no longer necessary, we
have removed that paragraph from this final rule.

Request To Revise Requirement To Determine Door Configuration

    Southwest Airlines (SWA) requested that we revise paragraph (o) of
the NPRM (77 FR 71723, December 4, 2012), which specified to ``Inspect
the door to determine the configuration, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1153, dated July 13, 2011.'' SWA considered that the intent of this
proposed requirement could be accomplished by records research instead
of a physical inspection. The commenter noted that the Accomplishment
Instructions of this service bulletin specify only identifying the part
number of the aft cargo door assembly, and does not specify a method of
accomplishment.
    We agree with the commenter that a records review is acceptable in
lieu of accomplishing an inspection to determine the configuration of
the door. We have changed paragraph (o) accordingly in this final rule.

Request To Refer To Revised Service Information

    All Nippon Airways (ANA) and Boeing requested that we revise the
NPRM (77 FR 71723, December 4, 2012) to also refer to Boeing Special
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3,
2011, in all locations where Boeing Service Bulletin 737-52-1154, dated
December 17, 2010, is cited. The commenters noted that some locations
of the NPRM referred to only the original version, but other paragraphs
referred to the original version ``as revised by Boeing Special
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3,
2011.''
    We agree with the commenter and have revised paragraphs (r)(2) and
(u)(2) in this final rule to also add ``as revised by Boeing Special
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3,
2011,'' after the original service bulletin citation.

Request To Clarify Access Procedures

    ANA noted that paragraph (s) of the NPRM (77 FR 71723, December 4,
2012) identified certain Parts in the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, for
compliance with the proposed requirements. ANA stated that Part 2,
which was not identified in paragraph (s) of the NPRM, provides access
procedures. ANA questioned whether the AD required specific procedures
for access.
    We agree, and have added new paragraph (u)(4) in this final rule to
clarify that the access and restoration procedures specified in the
referenced service information are not required by this AD.

Request To Clarify Required Part References for Compliance

    ANA noted that paragraph (t) of the NPRM (77 FR 71723, December 4,
2012) referred to Parts 1, 3, 4, 7, and 8 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-52A1153, dated July
13, 2011. Table 3 and Table 4 of that service bulletin also refer to
Parts 5 and 6 of that service bulletin. ANA questioned whether
operators might do Part 5 and Part 6, which describe the preventive
modification procedures, if no cracks are found. To avoid the need for
requests for alternative methods of compliance (AMOCs) regarding this
proposed requirement, ANA requested that we revise paragraph (t) of the
NPRM to clarify that compliance is ``in accordance with Parts 1, 2, 3,
4, 5, 6, 7, and 8'' of that service bulletin.
    We disagree with the commenter. Paragraph (s) requires actions in
accordance with Parts 5 and 6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011.
Paragraph (t) of this AD requires other actions, done in accordance
with Parts 1, 3, 4, 7, and 8 of that service bulletin. We find it
unnecessary to change this AD regarding this issue.

Request To Exclude Certain Supplemental Structural Inspections

    Paragraph (v) of the NPRM (77 FR 71723, December 4, 2012) would
provide relief from certain supplemental structural inspections
specified in Boeing Alert Service Bulletin 737-52A1153, dated July 13,
2011, and Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated
December

17, 2010. Boeing requested that we revise paragraph (v) of the NPRM to
also provide relief from the supplemental structural inspections
specified in Table 5 of paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 737-52-1154, dated December 17, 2010. Boeing noted
that the NPRM would require inspection of the adjacent cross beam if
cracks are found in the lower cross beam, and repair of any cracked
adjacent cross beam, in accordance with Boeing Service Bulletin 737-52-
1154, dated December 17, 2010, but the damage-tolerance inspections
associated with that repair are not mentioned.
    We agree with the request. We have revised paragraph (v) in this
final rule to also include reference to Table 5 of Boeing Service
Bulletin 737-52-1154, dated December 17, 2010.

Request To Delay Final Rule Pending Revised Service Information

    ANA stated that Boeing was in the process of revising Boeing
Service Bulletins 737-52-1153 and 737-52-1154 based on ANA's
validation. ANA requested that we cite the revised service information,
if it is available before the final rule is issued, to reduce
additional burden for Boeing and the operators. Boeing reported that
Boeing Service Bulletin 737-52-1154 was being revised to add extra
material to the repair parts to address issues regarding repair kits
found during the validation of the bulletin.
    We disagree to delay issuance of the final rule pending issuance of
revised service information. Accomplishing the service information
specified in this AD addresses the identified unsafe condition. When
the revised service bulletins are presented to us for review, however,
we might consider approving them as AMOCs for this AD. We have not
changed this final rule regarding this issue.

Additional Changes Made to This AD

    We have revised paragraph (v) and Note 2 to paragraph (v) of this
final rule. We have designated paragraph (v) as paragraph (v)(1) of
this final rule, and have reidentified Note 2 to paragraph (v) as
paragraph (v)(2) of this final rule.

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this 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 71723, December 4, 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 71723, December 4, 2012).
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 581 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:

                                                 Estimated Costs
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                                                                                Number of
            Action                Labor cost      Parts cost        Cost per      airplanes of     Cost on U.S.
                                                                    product       U.S. registry     operators
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Detailed inspection (retained  2 work-hours x               $0  $170 per                    494  $83,890 per
 action).                       $85 per hour =                   inspection                       inspection
                                $170 per                         cycle.                           cycle.
                                inspection
                                cycle.
High frequency eddy current    4 work-hours x                0  $340 per                    494  $167,960 per
 inspection (retained action).  $85 per hour =                   inspection                       inspection
                                $340 per                         cycle.                           cycle.
                                inspection
                                cycle.
Modification (retained         144 work-hours            5,430  $17,670........             494  $8,728,980.
 action).                       x $85 per hour
                                = $12,240.
Determination of door          1 work-hour x                 0  $85............             581  $49,385.
 configuration (new action).    $85 per hour =
                                $85.
Inspections (new action).....  6 work-hours x                0  $510 per                    581  $296,310 per
                                $85 per hour =                   inspection                       inspection
                                $510 per                         cycle.                           cycle.
                                inspection
                                cycle.
Modification (new action)....  59 work-hours x          30,536  $35,551........             \*\  Unknown.
                                $85 per hour =
                                $5,015.
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* The number of airplanes that require this modification depends on no cracking being found during a certain
  inspection.

    We estimate the following costs to do any necessary related
investigative and corrective actions that would be required based on
the results of the inspections. We have no way of determining the
number of aircraft that might need these actions:

                                               On-condition Costs
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                                                                                Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Related investigative and corrective actions..  59 work-hours x $85 per hour =           $30,536         $35,551
                                                 $5,015.
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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)
2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001), and
adding the following new AD:

2013-13-12 The Boeing Company: Amendment 39-17500 ; Docket No. FAA-
2012-1156; Directorate Identifier 2011-NM-205-AD.

(a) Effective Date

    This AD is effective September 10, 2013.

(b) Affected ADs

    This AD supersedes AD 2000-06-13 R1, Amendment 39-12317 (66 FR
36146, July 11, 2001).

(c) Applicability

    This AD applies to all The Boeing Company Model 737-200, -200C,
-300, -400, and -500 series airplanes, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 52, Doors.

(e) Unsafe Condition

    This AD was prompted by reports of cracking in the forward and
aft corner frame of the aft cargo door and in the lower cross beam.
We are issuing this AD to prevent fatigue cracking of the corners of
the door frame and the cross beams of the aft cargo door, which
could result in rapid depressurization of the airplane.

(f) Compliance

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

(g) Affected Airplanes for Retained Paragraphs

    Paragraphs (h), (i), (j), (k), and (l) of this AD are restated
from AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11,
2001). These paragraphs apply to Model 737-200 and -200C series
airplanes, line numbers 6 through 873 inclusive; and Model 737-200,
-200C, -300, and -400 series airplanes, line numbers 874 through
1642 inclusive; equipped with an aft cargo door having Boeing part
number (P/N) 65-47952-1 or P/N 65-47952-524, excluding airplanes
identified in paragraphs (g)(1) and (g)(2) of this AD.
    (1) Those airplanes on which that door has been modified as
specified in Boeing Service Bulletin 737-52-1079. Or,
    (2) Those airplanes on which the door assembly having P/N 65-
47952-524 includes four straps (P/Ns 65-47952-139, 65-47952-140, 65-
47952-141, and 65-47952-142) and a thicker lower cross beam web (P/N
65-47952-157).

(h) Retained Inspections and Corrective Actions

    This paragraph restates the actions required by paragraph (a) of
AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001),
with revised service information. For airplanes identified in
paragraph (g) of this AD: Within 90 days or 700 flight cycles after
December 24, 1998 (the effective date of AD 98-25-06, Amendment 39-
10931 (63 FR 67769, December 9, 1998)), whichever occurs later,
perform an internal detailed visual inspection to detect cracking of
the corners of the door frame and the cross beams of the aft cargo
door, in accordance with Boeing Service Bulletin 737-52-1079,
Revision 5, dated May 16, 1996; Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Boeing Alert
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
Accomplishment of the modification required by paragraph (l) of this
AD constitutes terminating action for the repetitive inspection
requirements of this paragraph. Doing the inspections required by
paragraph (p) or (s) of this AD terminates the inspections required
by this paragraph.
    (1) If no cracking is detected, accomplish the requirements of
either paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
    (i) Repeat the internal visual inspection thereafter at
intervals not to exceed 4,500 flight cycles. Or
    (ii) Prior to further flight, modify the corners of the door
frame and the cross beams of the aft cargo door, in accordance with
Boeing Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996;
Boeing Alert Service Bulletin 737-52A1079, Revision 6, dated
November 18, 1999; or Boeing Alert Service Bulletin 737-52A1079,
Revision 7, dated December 17, 2010. Accomplishment of such
modification constitutes terminating action for the repetitive
inspection requirements of paragraph (h)(1)(i) of this AD.
    (2) If any cracking is detected in the upper or lower cross
beams, prior to further flight, modify the cracked beam, in
accordance with Part I of the Accomplishment Instructions of Boeing
Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996; Part I
of the Accomplishment Instructions of Boeing Alert Service Bulletin
737-52A1079, Revision 6, dated November 18, 1999; or Part II of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Accomplishment of such
modification constitutes terminating action for the repetitive
inspection requirements of paragraph (h)(1)(i) of this AD for the
modified beam.
    (3) If any cracking is detected in the forward or aft upper door
frame, prior to further flight, repair the frame and modify the
corners of the door frame of the aft cargo door, in accordance with
Part I of the Accomplishment Instructions of Boeing Service Bulletin
737-52-1079, Revision 5, dated May 16, 1996; Part I of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Part II of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010; except as provided by
paragraph (i) of this AD. Accomplishment of such modification
constitutes terminating action for the repetitive inspection
requirements of paragraph (h)(1)(i) of this AD for the upper door
frame.
    (4) If any cracking is detected in the forward or aft lower door
frame, prior to further flight, replace the damaged frame with a new
frame, and modify the corners of the door frame of the aft cargo
door, in accordance with Part I of the Accomplishment Instructions
of Boeing Service Bulletin 737-52-1079, Revision 5, dated May 16,
1996; Part I of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1079, Revision 6, dated November 18, 1999;
or Part II of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
Accomplishment of such modification constitutes terminating

action for the repetitive inspection requirements of paragraph
(h)(1)(i) of this AD for the lower door frame.

(i) Retained Exception for Certain Actions Specified in Paragraphs (h)
and (l) of This AD

    This paragraph restates the requirement of paragraph (b) of AD
2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001). For
actions required by paragraphs (h) and (l) of this AD: Where Boeing
Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996; Boeing
Alert Service Bulletin 737-52A1079, Revision 6, dated November 18,
1999; or Boeing Alert Service Bulletin 737-52A1079, Revision 7,
dated December 17, 2010; specifies that certain repairs are to be
accomplished in accordance with instructions received from Boeing,
this AD requires that, prior to further flight, such repairs be
accomplished in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or using a method
approved in accordance with the procedures specified in paragraph
(x) of this AD.

(j) Retained Corrective Actions for Certain Cracking Found During
Inspection Required by Paragraph (h) of This AD

    This paragraph restates the corrective action required by
paragraph (c) of AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146,
July 11, 2001), with revised service information. If any cracking of
the outer chord of the upper or lower cross beams of the aft cargo
door is detected during any inspection required by paragraph (h) of
this AD, prior to further flight, accomplish the repair specified in
paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD. For a repair
method to be approved, as required by paragraphs (j)(1), (j)(3), and
(j)(4) of this AD, the approval letter must specifically reference
this AD.
    (1) Repair in accordance with a method approved by the Manager,
Seattle ACO.
    (2) Repair in accordance with Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Boeing Alert
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
    (3) Repair in accordance with data meeting the type
certification basis of the airplane approved by a Boeing Company
Designated Engineering Representative who has been authorized by the
FAA to make such findings.
    (4) Repair in accordance with a method approved by the Boeing
Commercial Airplanes Organization Designation Authorization (ODA)
whom we have authorized to make those findings.

(k) Retained Inspections and Corrective Actions for Airplanes
Identified in Paragraph (g) of This AD

    This paragraph restates the actions required by paragraph (d) of
AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001),
with revised service information. For airplanes identified in
paragraph (g) of this AD: Within 4,500 flight cycles or 1 year after
May 9, 2000 (the effective date of AD 2000-06-13, Amendment 39-11654
(65 FR 17583, April 4, 2000), whichever occurs later, perform a high
frequency eddy current inspection (HFEC) to detect cracking of the
four corners of the door frame of the aft cargo door, using a method
approved in accordance with the procedures specified in paragraph
(x) of this AD, or in accordance with Boeing Alert Service Bulletin
737-52A1079, Revision 6, dated November 18, 1999; or Boeing Alert
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
Accomplishment of the modification required by paragraph (l) of this
AD constitutes terminating action for the repetitive inspection
requirements of this paragraph. Doing the inspections required by
paragraph (p) or (s) of this AD terminates the inspections required
by this paragraph.

    Note 1 to paragraph (k) of this AD:  Additional guidance for the
inspection can be found in Boeing 737 Nondestructive Test Manual,
Part 6, Chapter 51-00-00 (Figure 4 or Figure 23).

    (1) If no cracking of the corners of the door frame of the aft
cargo door is detected, repeat the HFEC inspections thereafter at
intervals not to exceed 4,500 flight cycles until accomplishment of
the modification specified in paragraph (l) of this AD.
    (2) If any cracking of the corners of the door frame of the aft
cargo door is detected, prior to further flight, replace the damaged
frame with a new frame, and modify the four corners of the door
frame, in accordance with Part II and Part III of the Accomplishment
Instructions of Boeing Service Bulletin 737-52-1079, Revision 5,
dated May 16, 1996; Part II and Part III of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision
6, dated November 18, 1999; or Part III and Part IV of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Accomplishment of such
modification constitutes terminating action for the repetitive
inspection requirements of paragraph (k)(1) of this AD for that door
frame.

(l) Retained Terminating Action for Inspections Specified in Paragraphs
(h) and (k) of This AD

    This paragraph restates the action required by paragraph (e) of
AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001),
with revised service information. For airplanes identified in
paragraph (g) of this AD: Within 4 years or 12,000 flight cycles
after August 15, 2001 (the effective date of AD 2000-06-13 R1),
whichever occurs later, modify the four corners of the door frame
and the cross beams of the aft cargo door, in accordance with Part
II of the Accomplishment Instructions of Boeing Service Bulletin
737-52-1079, Revision 5, dated May 16, 1996; Part II of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Part III of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Accomplishment of that
modification constitutes terminating action for the repetitive
inspection requirements of paragraphs (h) and (k) of this AD.

(m) Retained Method of Compliance

    This paragraph restates the method of compliance of Note 3 of AD
2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001).
Accomplishment of the modification required by paragraph (a) of AD
90-06-02, Amendment 39-6489 (55 FR 8372, March 7, 1990), is
considered acceptable for compliance with the requirements of
paragraph (l) of this AD.

(n) Retained Credit for Previous Actions

    This paragraph restates the credit given for service information
specified in Note 4 of AD 2000-06-13 R1, Amendment 39-12317 (66 FR
36146, July 11, 2001). This paragraph provides credit for the
modification of the corners of the door frame and the cross beams of
the aft cargo door required by paragraph (l) of this AD, if the
modification was accomplished prior to August 15, 2001 (the
effective date of AD 2000-06-13 R1), using Boeing Service Bulletin
737-52-1079, dated December 16, 1983; Revision 1, dated December 15,
1988; Revision 2, dated July 20, 1989; Revision 3, dated May 17,
1990; or Revision 4, dated February 21, 1991.

(o) New Requirement for Determining Door Configuration

    At the applicable time specified in Table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1153, dated
July 13, 2011, except as provided by paragraph (u)(1) of this AD:
Inspect to determine the configuration of the aft cargo door, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1153, dated July 13, 2011. A review of
airplane maintenance records is acceptable in lieu of this
inspection if the configuration of the cargo door can be
conclusively determined from that review.

(p) New Requirements for Certain Doors Subject to Boeing Alert Service
Bulletin 737-52A1079, Revision 7, Dated December 17, 2010

    If, during the inspection required by paragraph (o) of this AD,
any door is determined to be from any airplane having line numbers 6
through 873 inclusive, and neither the modification nor the repair
specified in any service bulletin identified in paragraphs (p)(1)
through (p)(7) of this AD has been done as of the effective date of
this AD: Do a one-time HFEC and a one-time ultrasonic inspection for
cracking of the upper and lower corner frames and the upper and
lower cross beams, and do all applicable related investigative and
corrective actions, in accordance with Parts II, III, IV, and VI of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-52A1079, Revision 7, dated December 17, 2010; and, as
applicable, the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-52-1154, dated December 17, 2010, as
revised by Boeing Special Attention Service Bulletin 737-52-1154,
Revision 1, dated August 3, 2011; except as provided by paragraphs
(u)(2) and (u)(3) of this AD. Do the inspections before the
accumulation of 27,000 total flight cycles on the door, or within
4,500 door flight cycles after the

effective date of this AD, whichever occurs later (for airplanes on
which the door flight cycles are known); or within 4,500 flight
cycles after the effective date of this AD (for airplanes on which
door flight cycles are not known). Do all applicable related
investigative and corrective actions before further flight. If no
cracking is found during the initial inspections, before further
flight, do the modification in accordance with Part III of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Doing the inspection
specified in this paragraph terminates the inspections required by
paragraphs (h) and (k) of this AD.
    (1) Boeing Service Bulletin 737-52-1079, dated December 16,
1983.
    (2) Boeing Service Bulletin 737-52-1079, Revision 1, dated
December 15, 1988.
    (3) Boeing Service Bulletin 737-52-1079, Revision 2, dated July
20, 1989.
    (4) Boeing Service Bulletin 737-52-1079, Revision 3, dated May
17, 1990.
    (5) Boeing Service Bulletin 737-52-1079, Revision 4, dated
February 21, 1991.
    (6) Boeing Service Bulletin 737-52-1079, Revision 5, dated May
16, 1996.
    (7) Boeing Service Bulletin 737-52A1079, Revision 6, dated
November 18, 1999.

(q) Requirements for All Doors Subject to Boeing Alert Service Bulletin
737-52A1079, Revision 7, Dated December 17, 2010

    If, during the inspection required by paragraph (o) of this AD,
any door is determined to be from any airplane having line numbers 6
through 873 inclusive: Before the accumulation of 27,000 total
flight cycles on the door, or within 4,500 door flight cycles after
the effective date of this AD, whichever occurs later, (for
airplanes on which the door flight cycles are known); or within
4,500 flight cycles after the effective date of this AD (for
airplanes on which door flight cycles are not known); inspect the
lower corner frames to determine if the door has reinforcement
angles, P/N 65C25180-9, -43, -10, -11, or -12, that were installed
as specified in any service bulletin identified in paragraphs (q)(1)
through (q)(5) of this AD. If any affected reinforcement angle is
found, do a one-time general visual inspection for edge margin and
do a detailed inspection for cracks; in accordance with Part V of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-52A1079, Revision 7, dated December 17, 2010.
    (1) Boeing Service Bulletin 737-52-1079, dated December 16,
1983.
    (2) Boeing Service Bulletin 737-52-1079, Revision 1, dated
December 15, 1988.
    (3) Boeing Service Bulletin 737-52-1079, Revision 2, dated July
20, 1989.
    (4) Boeing Service Bulletin 737-52-1079, Revision 3, dated May
17, 1990.
    (5) Boeing Service Bulletin 737-52-1079, Revision 4, dated
February 21, 1991.

(r) Corrective Actions for Inspections Specified in Paragraph (q) of
This AD

    If, during any inspection required by paragraph (q) of this AD,
any crack is found, or if any edge margin does not meet the
specification identified in Part V of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision
7, dated December 17, 2010, before further flight, do the actions
specified in paragraphs (r)(1), (r)(2), and (r)(3) of this AD.
    (1) Replace the corner reinforcement angle, in accordance with
Part III of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
    (2) Do a one-time detailed inspection or HFEC inspection for
cracking at the forward and aft ends of cross beam D, in accordance
with Part 1 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-52-1154, dated December 17, 2010; or
Boeing Special Attention Service Bulletin 737-52-1154, dated
December 17, 2010, as revised by Boeing Special Attention Service
Bulletin 737-52-1154, Revision 1, dated August 3, 2011. If any
cracking is found, before further flight, do all applicable repairs
in accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-52-1154, dated December 17, 2010; or
Boeing Special Attention Service Bulletin 737-52-1154, dated
December 17, 2010, as revised by Boeing Special Attention Service
Bulletin 737-52-1154, Revision 1, dated August 3, 2011, except as
provided by paragraph (u)(2) of this AD.
    (3) Do a one-time detailed inspection or ultrasonic inspection
for cracking on the frames, in accordance with Part 2 (detailed
inspection) or Part 8 (ultrasonic inspection) of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 737-52-
1154, dated December 17, 2010, as revised by Boeing Special
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3,
2011. If any cracking is found, before further flight, replace the
frame in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-52A1079, Revision 7, dated December 17,
2010.

(s) Requirements for Doors Subject to Boeing Alert Service Bulletin
737-52A1153, Dated July 13, 2011

    If, during the action required by paragraph (o) of this AD, a
door is determined to be from an airplane having line numbers 874
and subsequent: At the applicable time specified in Tables 1 and 2
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1153, dated July 13, 2011, except as provided by paragraph
(u)(1) of this AD, do high frequency and detailed inspections for
cracks in the forward and aft ends of cross beam E, and do all
applicable related investigative and corrective actions, in
accordance with Parts 1, 3, 4, 5, and 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-52A1153, dated
July 13, 2011; and, as applicable, the Accomplishment Instructions
of Boeing Special Attention Service Bulletin 737-52-1154, dated
December 17, 2010, as revised by Boeing Special Attention Service
Bulletin 737-52-1154, Revision 1, dated August 3, 2011; except as
provided by paragraph (u)(2) of this AD. Do all applicable related
investigative and corrective actions at the applicable time
specified in Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011,
except as provided by paragraph (u)(1) of this AD. If no cracking is
found during the inspections specified in Boeing Alert Service
Bulletin 737-52A1153, dated July 13, 2011, at the applicable time
specified in Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011,
except as provided by paragraph (u)(1) of this AD, do the
modification in accordance with Parts 5 and 6, as applicable, of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1153, dated July 13, 2011. Repeat the inspections thereafter at
the times specified in Tables 1 and 2 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1153, dated
July 13, 2011, until the preventative modification or repair is done
to both ends of cross beam E in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-52A1153, dated
July 13, 2011. Doing the inspection specified in this paragraph
terminates the inspections required by paragraphs (h) and (k) of
this AD.

(t) One Time Inspections for Doors Subject to Boeing Alert Service
Bulletin 737-52A1153, Dated July 13, 2011

    If, during the actions required by paragraph (o) of this AD, a
door is determined to be from an airplane having line numbers 874
and subsequent: At the applicable time specified in Tables 3 and 4
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1153, dated July 13, 2011, except as provided by paragraph
(u)(1) of this AD, do a one-time ultrasonic inspection of the frame
and a detailed inspection of the reinforcing angle for cracks of the
forward and aft ends of cross beam E, and do all applicable related
investigative and corrective actions, in accordance with Parts 1, 3,
4, 7, and 8 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1153, dated July 13, 2011; and, as
applicable; the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-52-1154, dated December 17, 2010, as
revised by Boeing Special Attention Service Bulletin 737-52-1154,
Revision 1, dated August 3, 2011; except as provided by paragraph
(u)(2) of this AD. Do all applicable related investigative and
corrective actions before further flight.

(u) Service Information Exceptions

    The following exceptions apply to this AD.
    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-52A1153, dated July 13, 2011, specifies a
compliance time ``after the original issue date of this service
bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
    (2) Where Boeing Special Attention Service Bulletin 737-52-1154,
dated December 17, 2010; and Boeing Special Attention Service
Bulletin 737-52-1154, dated December 17, 2010, as revised by Boeing
Special Attention Service Bulletin 737-52-1154, Revision 1, dated
August 3, 2011, specify to contact Boeing for repair, before further
flight, repair using a method approved in accordance with the
procedures specified in paragraph (x) of this AD.

    (3) Where Boeing Alert Service Bulletin 737-52A1079, Revision 7,
dated December 17, 2010, specifies to contact Boeing for repair,
before further flight, repair using a method approved in accordance
with the procedures specified in paragraph (x) of this AD.
    (4) This AD does not require accomplishment of the access and
restoration procedures identified in the Work Instructions of Boeing
Alert Service Bulletin 737-52A1079, Revision 7, dated December 17,
2010; Boeing Alert Service Bulletin 737-52A1153, dated July 13,
2011; Boeing Special Attention Service Bulletin 737-52-1154, dated
December 17, 2010; and Boeing Special Attention Service Bulletin
737-52-1154, dated December 17, 2010, as revised by Boeing Special
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3,
2011.

(v) Supplemental Structural Inspections

    (1) The supplemental structural inspections specified in Tables
5 and 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-52A1153, dated July 13, 2011; and Tables 3 and 4 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1079, Revision 7, dated December 17, 2010; and Table 5 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-52-
1154, dated December 17, 2010, as revised by Boeing Special
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3,
2011, are not required by this AD.
    (2) The damage tolerance inspections specified in Tables 5 and 6
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1153, dated July 13, 2011; and Tables 3 and 4 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-52A1079,
Revision 7, dated December 17, 2010; and Table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 737-52-1154, dated
December 17, 2010, as revised by Boeing Special Attention Service
Bulletin 737-52-1154, Revision 1, dated August 3, 2011; may be used
in support of compliance with section 121.1109(c)(2) or
129.109(b)(2) of the Federal Aviation Regulations (14 CFR
121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions
specified in the Accomplishment Instructions and figures of Boeing
Alert Service Bulletin 737-52A1153, dated July 13, 2011; and Boeing
Alert Service Bulletin 737-52A1079, Revision 7, dated December 17,
2010; are not required by this AD.

(w) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by
paragraphs (p), (q), and (r) of this AD, if the actions were
accomplished before the effective date of this AD using any service
information specified in paragraph (w)(1)(i), (w)(1)(ii),
(w)(1)(iii), (w)(1)(iv), (w)(1)(v), (w)(1)(vi), or (w)(1)(vii) of
this AD.
    (i) Boeing Service Bulletin 737-52-1079, dated December 16,
1983.
    (ii) Boeing Service Bulletin 737-52-1079, Revision 1, dated
December 15, 1988.
    (iii) Boeing Service Bulletin 737-52-1079, Revision 2, dated
July 20, 1989.
    (iv) Boeing Service Bulletin 737-52-1079, Revision 3, dated May
17, 1990.
    (v) Boeing Service Bulletin 737-52-1079, Revision 4, dated
February 21, 1991.
    (vi) Boeing Service Bulletin 737-52-1079, Revision 5, dated May
16, 1996.
    (vii) Boeing Alert Service Bulletin 737-52A1079, Revision 6,
dated November 18, 1999.
    (2) This paragraph provides credit for actions required by
paragraphs (s) and (t) of this AD, if the actions were accomplished
before the effective date of this AD using Boeing Service Bulletin
737-52-1154, dated December 17, 2010, provided that any alternative
detailed inspections specified in Part 17 of the Accomplishment
Instructions of Boeing Service Bulletin 737-52-1154, dated December
17, 2010, were done in accordance with Part 11 of the Accomplishment
Instructions of Boeing Service Bulletin 737-52-1154, dated December
17, 2010.

(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 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 2000-06-13,
Amendment 39-11654 (65 FR 17583, April 4, 2000); and AD 2000-06-13
R1, Amendment 39-12317 (66 FR 36146, July 11, 2001); are approved as
AMOCs for the corresponding requirements of this AD.

(y) Related Information

    For more information about this AD, contact Alan Pohl, 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>
(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 for IBR on
September 10, 2013.
    (i) Boeing Alert Service Bulletin 737-52A1153, dated July 13,
2011.
    (ii) Boeing Alert Service Bulletin 737-52A1079, Revision 7,
dated December 17, 2010.
    (iii) Boeing Special Attention Service Bulletin 737-52-1154,
dated December 17, 2010.
    (iv) Boeing Special Attention Service Bulletin 737-52-1154,
Revision 1, dated August 3, 2011.
    (4) The following service information was approved for IBR on
May 9, 2000 (65 FR 17583, April 4, 2000).
    (i) Boeing Alert Service Bulletin 737-52A1079, Revision 6, dated
November 18, 1999.
    (ii) Reserved.
    (5) The following service information was approved for IBR on
December 24, 1998 (63 FR 67769, December 9, 1998).
    (i) Boeing Service Bulletin 737-52-1079, Revision 5, dated May
16, 1996.
    (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<PHONE_NUMBER>; Internet https://www.myboeingfleet.com.
    (7) You may view this service information at FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington
98057-3356. For information on the availability of this material at
the FAA, call<PHONE_NUMBER>.
    (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<PHONE_NUMBER>, or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 18, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-18765 Filed 8-5-13; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 76, Number 227 (Friday, November 25, 2011)]
[Notices]
[Pages 72700-72702]
[FR Doc No: 2011-30360]

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ENVIRONMENTAL PROTECTION AGENCY

[EPA-HQ-OAR-2011-0901; FRL-9496-6]

Agency Information Collection Activities; Proposed Collections;
Comment Request; Prevention of Significant Deterioration and
Nonattainment Area New Source Review (Renewal)

AGENCY: Environmental Protection Agency (EPA).

ACTION: Notice.

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SUMMARY: In compliance with the Paperwork Reduction Act (PRA) (44
U.S.C. 3501 et seq.), this document announces that EPA is planning to
submit a request to renew an existing approved Information Collection
Request (ICR) to the Office of Management and Budget (OMB). This ICR is
scheduled to expire on April 30, 2012. Before submitting this ICR to
OMB for review and approval, EPA is soliciting comments on specific
aspects of the proposed information collection as described below.

DATES: Comments must be submitted on or before January 24, 2012.

ADDRESSES: Submit your comments, identified by Docket ID No. EPA-HQ-
OAR-2011-0901, by one of the following methods:
     http://www.regulations.gov: Follow the on-line
instructions for submitting comments.
     Email<EMAIL_ADDRESS>     Fax:<PHONE_NUMBER>.
     Mail: Agency Information Collection Activities; Proposed
Collection; Comment Request; Prevention of Significant Deterioration
and Nonattainment Area New Source Review (Renewal) Docket,
Environmental Protection Agency, Air and Radiation Docket and
Information Center, Mailcode: 2822T, 1200 Pennsylvania Ave. NW.,
Washington, DC 20460. Please include a total of two copies.
     Hand Delivery: EPA Docket Center, Public Reading Room, EPA
West, Room 3334, 1301 Constitution Ave. NW., Washington, DC 20460. Such
deliveries are only accepted during the Docket's normal hours of
operation, and special arrangements should be made for deliveries of
boxed information.
    Instructions: Direct your comments to Docket ID No. EPA-HQ-OAR-
2011-0901. The EPA's policy is that all comments received will be
included in the public docket without change and may be made available
online at http://www.regulations.gov, including any personal
information provided, unless the comment includes information claimed
to be Confidential Business Information (CBI) or other information
whose disclosure is restricted by statute. Do not submit information
that you consider to be CBI or otherwise protected through http://www.regulations.gov or email. The http://www.regulations.gov Web site
is an ``anonymous access'' system, which means the EPA will not know
your identity or contact information unless you provide it in the body
of your comment. If you send an email comment directly to the EPA
without going through http://www.regulations.gov, your email address
will be automatically captured and included as part of the comment that
is placed in the public docket and made available on the Internet. If
you submit an electronic comment, the EPA recommends that you include
your name and other contact information in the body of your comment and
with any disk or CD-ROM you submit. If the EPA cannot read your comment
due to technical difficulties and cannot contact you for clarification,
the EPA may not be able to consider your comment. Electronic files
should avoid the use of special characters, any form of encryption and
be free of any defects or viruses. For additional information about the
EPA's public docket visit the EPA Docket Center homepage at http://www.epa.gov/epahome/dockets.htm.

FOR FURTHER INFORMATION CONTACT: Mr. David Painter, Air Quality Policy
Division, Office of Air Quality Planning and Standards (C504-03),
Environmental Protection Agency, Research Triangle Park, North Carolina
27711; telephone number:<PHONE_NUMBER>; fax number:<PHONE_NUMBER>;
email address<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

How can I access the docket and/or submit comments?

    The EPA has established a public docket for this ICR under Docket
ID No. EPA-HQ-OAR-2011-0901, which is available for online viewing at
http://www.regulations.gov, or in person viewing at the Air and
Radiation Docket in the EPA Docket Center (EPA/DC), EPA West, Room
3334, 1301 Constitution Ave. NW., Washington, DC. The EPA/DC Public
Reading Room is open from 8:30 a.m. to 4:30 p.m., Monday through
Friday, excluding legal

holidays. The telephone number for the Public Reading Room is (202)
566-1744.
    Use http://www.regulations.gov to obtain a copy of the draft
collection of information, submit or view public comments, access the
index listing of the contents of the docket and access those documents
in the public docket that are available electronically. Once in the
system, select ``search,'' then key in the docket ID number identified
in this document.

What information is EPA particularly interested in?

    Pursuant to section 3506(c)(2)(A) of the PRA, the EPA specifically
solicits comments and information to enable it to:
    (i) Evaluate whether the proposed collection of information is
necessary for the proper performance of the functions of the agency,
including whether the information will have practical utility;
    (ii) Evaluate the accuracy of the agency's estimate of the burden
of the proposed collection of information, including the validity of
the methodology and assumptions used;
    (iii) Enhance the quality, utility and clarity of the information
to be collected; and
    (iv) Minimize the burden of the collection of information on those
who are to respond, including through the use of appropriate automated
electronic, mechanical or other technological collection techniques or
other forms of information technology, e.g., permitting electronic
submission of responses. In particular, the EPA is requesting comments
from very small businesses (those that employ less than 25) on examples
of specific additional efforts that the EPA could make to reduce the
paperwork burden for very small businesses affected by this collection.

What should I consider when I prepare my comments for EPA?

    You may find the following suggestions helpful for preparing your
comments:
    1. Explain your views as clearly as possible and provide specific
examples.
    2. Describe any assumptions that you used.
    3. Provide copies of any technical information and/or data you used
that support your views.
    4. If you estimate potential burden or costs, explain how you
arrived at the estimate that you provide.
    5. Offer alternative ways to improve the collection activity.
    6. Make sure to submit your comments by the deadline identified
under DATES.
    7. To ensure proper receipt by the EPA, be sure to identify the
docket ID number assigned to this action in the subject line on the
first page of your response. You may also provide the name, date, and
Federal Register citation.

What information collection activity does this apply to?

    Affected entities: Entities potentially affected by this action are
those which must apply for and obtain a preconstruction permit under
part C or D or section 110(a)(2)(C) of title I of the Clean Air Act
(Act).
    Title: Prevention of Significant Deterioration and Nonattainment
Area New Source Review (Renewal).
    ICR number: EPA ICR No. 1230.29, OMB Control No. 2060-0003.
    ICR status: This ICR is scheduled to expire on April 30, 2012.
    Abstract: Part C of the Clean Air Act (Act)--``Prevention of
Significant Deterioration,'' and Part D--``Plan Requirements for
Nonattainment Areas,'' require all states to adopt preconstruction
review programs for new or modified stationary sources of air
pollution. In addition, the provisions of section 110 of the Act
include a requirement for states to have a preconstruction review
program to manage the emissions from the construction and modification
of any stationary source of air pollution to assure that the National
Ambient Air Quality Standards (NAAQS) are achieved and maintained. An
agency may not conduct or sponsor, and a person is not required to
respond to, a collection of information request unless it displays a
currently valid OMB control number. The OMB control numbers for the
EPA's regulations in 40 CFR are listed in 40 CFR part 9 and 48 CFR
chapter 15. Section 176(c) of the Clean Air Act (42 U.S.C. 7401 et
seq.) requires that all Federal actions conform with the state
implementation plans (SIPs) to attain and maintain the NAAQS. Depending
on the type of action, the Federal entities must collect information
themselves, hire consultants to collect the information, or require
applicants/sponsors of the Federal action to provide the information.
    Implementing regulations for these three programs are promulgated
at 40 CFR 51.160 through 51.166; 40 CFR part 51, Appendix S; and 40 CFR
52.21 and 52.24. In order to receive a construction permit for a major
new source or major modification, the applicant must conduct the
necessary research, perform the appropriate analyses and prepare the
permit application with documentation to demonstrate that their project
meets all applicable statutory and regulatory New Source Review
requirements. Specific activities and requirements are listed and
described in the Supporting Statement for the ICR.
    State, local, or Federal reviewing authorities review permit
applications and provide for public review of proposed projects and
issue permits based on their consideration of all technical factors and
public input. The EPA, more broadly, reviews a fraction of the total
applications and audits the state and local programs for their
effectiveness. Consequently, information prepared and submitted by
sources is essential for sources to receive permits, and for Federal,
state, and local environmental agencies to adequately review the permit
applications and thereby properly administer and manage the NSR
programs.
    Since the previous renewal of this ICR, the EPA has filled
regulatory voids that existed in Indian country (where state NSR
programs do not apply) by promulgating a Part D program and a minor NSR
program for Indian country. (The EPA was already implementing a Part C
program in Indian country.) The implementing regulations for these
programs are at 40 CFR 49.151 through 49.173. The EPA acts as the
reviewing authority for these programs.
    Information that is collected is handled according to EPA's
policies set forth in title 40, chapter 1, part 2, subpart B--
Confidentiality of Business Information (see 40 CFR part 2). See also
section 114(c) of the Act.
    Burden Statement: Burden means the total time, effort or financial
resources expended by persons to generate, maintain, retain or disclose
or provide information to or for a Federal agency. This includes the
time needed to review instructions; develop, acquire, install and
utilize technology and systems for the purposes of collecting,
validating and verifying information, processing and maintaining
information and disclosing and providing information; adjust the
existing ways to comply with any previously applicable instructions and
requirements; train personnel to be able to respond to a collection of
information; search data sources; complete and review the collection of
information; and transmit or otherwise disclose the information.
    The annual public reporting and recordkeeping burden for this
collection of information is broken down as follows:

----------------------------------------------------------------------------------------------------------------
                   Type of permit action                        Major PSD       Major Part D          Minor
----------------------------------------------------------------------------------------------------------------
State Programs:
    Number of Sources.....................................             1,610               486            72,841
    Burden Hours per Response
        Industry..........................................             1,006               642                39
        Reviewing Authorities.............................               336               128                29
    Total Annual Burden Hours:
        Industry..........................................         1,619,660           312,012         2,822,885
        Reviewing Authorities.............................           540,960            62,208         2,095,140
Indian Country Program:
    Number of Sources.....................................                 a                 a            12,432
    Industry Burden Hours per Response....................                 a                 a                39
    Industry Total Annual Burden Hours....................                 a                 a           479,435
----------------------------------------------------------------------------------------------------------------
Any minor discrepencies are due to rounding.
\a\ The PSD and Part D programs in Indian country are included in the state program figures.

    In addition, we estimate that the 112 state and local reviewing
authorities will prepare and submit an average of 51 SIP revisions per
year to conform to changes in the NSR regulations, for a total annual
burden of 2,040 hours. Besides the burden hours tallied above for
permitting and SIP revisions, we estimate that 34 of the sources
subject to PSD permitting are required to conduct pre-construction
monitoring which they outsource, representing start-up costs totaling
$12,444,204.
    Respondents/Affected Entities: Industrial plants; state and local
reviewing authorities.
    Estimated Number of Respondents: 87,481, including 87,369 industry
sources and 112 state and local reviewing authorities generating a
total of 162,357 responses.
    Estimated Total Annual Burden: 7,934,340 hours and $12,444,204.

Are there changes in the estimates from the last approval?

    Since the last renewal of this ICR (October 2008), the estimated
number of responses has increased by 11,536 due primarily to the
addition of the minor NSR program for Indian country which requires all
existing minor sources to register within the first 3 years of the
program. In addition, actions under the Act unrelated to NSR rule
changes brought greenhouse gases into the prevention of significant
deterioration (PSD) program, but the potentially overwhelming increase
in permit actions that this might have caused was limited to a
manageable level (fewer than 1,350 sources) by the Greenhouse Gas
Tailoring Rule. Partially counteracting these increases, the Flexible
Air Permitting Rule had the effect of reducing the number of
respondents under the PSD, Part D, and minor NSR programs.
    The burden per PSD permit has increased due to the addition of
greenhouse gases to the program. In addition, provisions were added to
the PSD regulations that allow for full implementation of the program
for particulate matter less than 2.5 micrograms (PM2.5),
which has resulted in an increase in the modeling required for PSD
permits and, thus, an increase in the per-permit burden. The Flexible
Air Permitting Rule marginally increased the per-permit burden for the
PSD and Part D programs, although the overall effect of the rule was to
reduce total burden because of the reduction in the number of permit
actions. The Flexible Air Permitting Rule also slightly reduced the
burden per minor NSR permit.
    As a result of all these changes to the NSR program, the total
burden for the program has increased by 1,983,272 hours.

What is the next step in the process for this ICR?

    The EPA will consider the comments received and amend the ICR as
appropriate. The final ICR package will then be submitted to OMB for
review and approval pursuant to 5 CFR 1320.12. At that time, EPA will
issue another Federal Register notice pursuant to 5 CFR
1320.5(a)(1)(iv) to announce the submission of the ICRs to OMB and the
opportunity to submit additional comments to OMB. If you have any
questions about this ICR or the approval process, please contact the
technical person listed under FOR FURTHER INFORMATION CONTACT.

    Dated: November 21, 2011.
Mary Henigin,
Acting, Office of Air Quality Planning and Standards.
[FR Doc. 2011-30360 Filed 11-23-11; 8:45 am]
BILLING CODE 6560-50-P


[Federal Register Volume 79, Number 27 (Monday, February 10, 2014)]
[Notices]
[Pages 7661-7662]
[FR Doc No: 2014-02741]

-----------------------------------------------------------------------

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 4609-007]

New Hampshire Wood Products Company Bath Electric Power Company
LLC; Notice of Transfer of Exemption

    1. By letter filed November 26, 2013, Bath Electric Power Company
LLC parent company of New Hampshire Wood Products Company informed the
Commission that the exemption from licensing for the Ammonoosuc River
Dam Project, FERC No. 4609, originally issued January 11, 1982,\1\ has
been

transferred to Bath Electric Power Company LLC. The project is located
on the Ammonoosuc River in Grafton County, New Hampshire. The transfer
of an exemption does not require Commission approval.
---------------------------------------------------------------------------

    \1\ 18 FERC ] 62,026, Notice of Approval by Operation of Law.
---------------------------------------------------------------------------

    2. Bath Electric Power Company LLC is now the exemptee of the
Ammonoosuc River Dam Project, FERC No. 4609. All correspondence should
be forwarded to: Bath Electric Power Company LLC, 112 Terrace Drive,
North Haverhill, NH 03774.

    Dated: Issued February 3, 2014.
Kimberly D. Bose,
Secretary.
[FR Doc. 2014-02741 Filed 2-7-14; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 80, Number 79 (Friday, April 24, 2015)]
[Proposed Rules]
[Pages 22943-22946]
[FR Doc No: 2015-09549]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0926; Directorate Identifier 2014-NM-121-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 97-07-14,
for certain Airbus Model A320-111, -211, and -231 airplanes. AD 97-07-
14 currently requires modification of an area on the front spar of the
wing center section by installing shims and new fasteners to reinforce
pressure floor fittings. Since we issued AD 97-07-14, we have
determined the need for repetitive inspections on airplanes on which
the modification of the rib flange on the front spar of the wing center
section has been done. This proposed AD would continue to require
modifying the rib flange on the front spar of the wing center section
by installing shims and new fasteners to reinforce pressure floor
fittings; and would require repetitive high frequency eddy current
inspections for cracking of the radius of the rib flanges and vertical
stiffener at frame 36, a rototest inspection for cracking of the
fastener holes of the rib flanges, repair if needed, and adding
additional airplanes to the applicability. We are proposing this AD to
prevent fatigue cracking on the rib flange area of the front spar of
the wing center section, which can reduce the structural integrity of
fuselage frame 36 and the wing center section.

DATES: We must receive comments on this proposed AD by June 8, 2015.

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:<PHONE_NUMBER>.
     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, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email<EMAIL_ADDRESS>Internet http://www.airbus.com. You may view this 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 by searching for and locating Docket No. FAA-2015-
0926; 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
Operations office (telephone<PHONE_NUMBER>) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone<PHONE_NUMBER>;
fax<PHONE_NUMBER>.

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-2015-0926;
Directorate Identifier 2014-NM-121-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 based on 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 27, 1997, we issued AD 97-07-14, Amendment 39-9988 (62 FR
16473, April 7, 1997). AD 97-07-14 requires modification of an area on
the front spar of the wing center section by installing shims and new
fasteners to reinforce pressure floor fittings on certain Airbus Model
A320-111, -211 and -231 airplanes.
    Since we issued AD 97-07-14, Amendment 39-9988 (62 FR 16473, April
7, 1997), we have determined the need for repetitive inspections on
airplanes on which Airbus Modification 20976 (modification of the rib
flange on the front spar of the wing center section) was done in
production, or was done using Airbus Service Bulletin A320-57-1013,
dated April 12, 1989; or Airbus Service Bulletin A320-57-1013, Revision
1, dated September 29, 1992.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent

for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0053, dated March 7, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on certain Airbus Model
A320-211 and -231 airplanes. The MCAI states:

    During full scale fatigue tests on the Airbus A320 test
specimen, cracks were found in the rib flange on the front spar side
perpendicular to vertical posts at frame (FR) 36. It was determined
that similar cracks could develop on certain in-service aeroplanes.
    This condition, if not detected and corrected, could affect the
wing structural integrity.
    To reduce the risk of crack initiation, two modifications for
aeroplanes in production and one modification for in-service
aeroplanes were developed by Airbus: Prior to [manufacturer serial
number] MSN 0085, the adaptation modification (Mod) 20976 was
applied in production, consisting in installing shims under the
fasteners linking the rib flange, the lower corner, the front spar
and its vertical stiffener; from MSN 0085 onwards, the serial Mod
20908 was applied in production, consisting in installing reinforced
lower surface rib flanges at front spar level.
    Airbus issued Service Bulletin (SB) A320-57-1013 for affected
in-service aeroplanes, and [Directorate General for Civil Aviation]
DGAC France issued AD 95-098-066 [which corresponds to FAA AD 97-07-
14, Amendment 39-9988, (62 FR 16473, April 7, 1997)] to require
installation of shims under the fasteners linking the rib flange,
the lower corner, the front spar and its vertical stiffener.
    Following a recent analysis, Airbus identified the need for
repetitive [HFEC and rototest] inspections for aeroplanes on which
Airbus SB A320-57-1013 or production Mod 20976 has been embodied.
    For the reason described above, this [EASA] AD retains the
requirements of DGAC France AD 95-098-066, which is superseded, and
requires repetitive [HFEC and rototest] inspections of the center
wing lower ribs at FR 36 and, depending on findings, accomplishment
of a repair.
    After EASA issued PAD 14-013, it was discovered that additional
work [removal of shims and fasteners on the rib flange on the front
spar side and doing an HFEC inspection for cracking of the radius of
the rib flanges and a rototest inspection for cracking of the
fastener holes during each inspection] to be included in Revision 01
of Airbus SB A320-57-1175, is required to accomplish the
inspections. This Final [EASA] AD has been amended accordingly.

    Airplanes having MSNs 001, 009, and 015 were not included in the
applicability of AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7,
1997). EASA AD 2014-0053, dated March 7, 2014, expanded the
applicability to all airplanes having up to MSN 0084. We included
paragraph (h) of this proposed AD to require the modification for the
airplanes having MSNs 001, 009, and 015.You may examine the MCAI in the
AD docket on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2015-0926.

Related Service Information Under 1 CFR part 51

    Airbus has issued Service Bulletin A320-57-1175, Revision 01,
including Appendix 01 and Appendix 02, dated May 28, 2014. The service
information describes procedures for repetitive high frequency eddy
current inspections for cracking of the radius of the rib flanges and
vertical stiffener at frame 36, a rototest inspection for cracking of
the fastener holes of the rib flanges, and repair. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI. This service information is
reasonably available; see ADDRESSES for ways to access this service
information.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the
Airworthiness Directives Implementation Aviation Rulemaking Committee
(AD ARC), to enhance the AD system. One enhancement was a new process
for annotating which procedures and tests in the service information
are required for compliance with an AD. Differentiating these
procedures and tests from other tasks in the service information is
expected to improve an owner's/operator's understanding of crucial AD
requirements and help provide consistent judgment in AD compliance. The
actions specified in the service information identified previously
include procedures and tests that are identified as RC (required for
compliance) because these procedures have a direct effect on detecting,
preventing, resolving, or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the
specified service information, procedures and tests identified as RC
must be done to comply with the proposed AD. However, procedures and
tests that are not identified as RC are recommended. Those procedures
and tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an alternative method
of compliance (AMOC), provided the procedures and tests identified as
RC can be done and the airplane can be put back in a serviceable
condition. Any substitutions or changes to procedures or tests
identified as RC will require approval of an AMOC.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.

Differences Between the AD and the MCAI or Service Information

    Although Airbus Service Bulletin A320-57-1175, Revision 01,
including Appendix 01 and Appendix 02, dated May 28, 2014, specifies to
contact the manufacturer for instructions on how to repair certain
conditions, this proposed AD would require repairing those conditions
using a method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or EASA or its delegated agent, or
Airbus' EASA Design Organization Approval (DOA).

Costs of Compliance

    We estimate that this proposed AD affects 11 airplanes of U.S.
registry.
    The actions required by AD 97-07-14, Amendment 39-9988 (62 FR
16473, April 7, 1997), and retained in this proposed AD take about 13
work-hours per product, at an average labor rate of $85 per work-hour.
Required parts cost about $576 per product. Based on these figures, the
estimated cost of the actions that are required by AD 97-07-14 is
$1,681 per product.
    We also estimate that it would take about 45 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $1,600
per product. Based on these figures, we estimate the cost of this
proposed AD on U.S. operators to be $59,675, or $5,425 per product.

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 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.
    For the reasons discussed above, I certify this 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);
    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.

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

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)
97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997), and adding
the following new AD:

Airbus: Docket No. FAA-2015-0926; Directorate Identifier 2014-NM-
121-AD.

(a) Comments Due Date

    We must receive comments by June 8, 2015.

(b) Affected ADs

    This AD replaces AD 97-07-14, Amendment 39-9988 (62 FR 16473,
April 7, 1997).

(c) Applicability

    This AD applies to Airbus Model A320-211 and -231 airplanes,
certificated in any category, all manufacturer serial numbers (MSN)
up to MSN 0084 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by the determination that repetitive
inspections are needed on airplanes on which the modification of the
rib flange on the front spar of the wing center section has been
done. We are issuing this AD to prevent fatigue cracking on the rib
flange area of the front spar of the wing center section, which can
reduce the structural integrity of fuselage frame 36 and the wing
center section.

(f) Compliance

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

(g) Retained Modification

    This paragraph restates the requirements of paragraph (a) of AD
97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997). For
airplanes with manufacturer serial number (MSN) 005 through 008
inclusive, MSN 010 through 014 inclusive, and MSN 016 through 042
inclusive: Prior to the accumulation of 16,000 total landings, or
within 3 months after May 12, 1997 (the effective date of AD 97-07-
14), whichever occurs later, modify the rib flange on the front spar
of the wing center section by installing shims and new fasteners to
reinforce pressure floor fittings, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-57-1013,
Revision 1, dated September 29, 1992.

(h) Modification for Airplanes With MSNs 001, 009, and 015

    Prior to the accumulation of 16,000 total landings since first
flight, or within 30 days after the effective date of this AD,
whichever occurs later, modify the rib flange on the front spar of
the wing center section by installing shims and new fasteners to
reinforce pressure floor fittings, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-57-1013,
Revision 1, dated September 29, 1992.

(i) New Requirement of This AD: Repetitive Inspections

    Within the applicable compliance times specified in paragraphs
(i)(1) and (i)(2) of this AD, do a high frequency eddy current
(HFEC) inspection for cracking of the radius of the rib flanges and
vertical stiffener at frame 36 and do a rototest inspection for
cracking of the fastener holes of the rib flanges and vertical
stiffener, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-57-1175, Revision 01, including
Appendix 01, dated May 28, 2014. During each inspection, remove the
shims and fasteners on the rib flange on the front spar side and do
an HFEC inspection for cracking of the radius of the rib flanges and
a rototest inspection for cracking of the fastener holes. If no
cracking is found, oversize the holes of the rib flange and the
holes of the shims, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-57-1175, Revision 01,
including Appendix 01, dated May 28, 2014. Repeat the inspections
thereafter at intervals not to exceed 32,500 flight cycles or 65,000
flight hours, whichever occurs first.
    (1) For airplanes having Airbus Modification 20976 embodied: At
the later of the times specified in paragraphs (i)(1)(i) or
(i)(1)(ii) of this AD.
    (i) Before exceeding 47,800 flight cycles or 95,600 flight
hours, whichever occurs first, since the airplane's first flight.
    (ii) Within 850 flight cycles or 1,700 flight hours, whichever
occurs first, after the effective date of this AD.
    (2) For airplanes on which the modification of the front spar of
the wing center section was accomplished using Airbus Service
Bulletin A320-57-1013, Revision 1, dated September 29, 1992: At the
later of the times specified in paragraphs (i)(2)(i) or (i)(2)(ii)
of this AD.
    (i) Before exceeding 10,700 flight cycles or 21,500 flight
hours, whichever occurs first, after the modification of the rib
flange on the front spar of the wing center section was done using
Airbus Service Bulletin A320-57-1013, Revision 1, dated September
29, 1992.
    (ii) Within 850 flight cycles or 1,700 flight hours, whichever
occurs first, after the effective date of this AD.

(j) Repair

    If, during any inspection required by paragraph (i) of this AD,
any cracking is found, before further flight, repair using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA).

(k) Credit for Previous Actions

    This paragraph restates the requirements of Note 2 of paragraph
(g) of AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997):
This paragraph provides credit for the modification of the rib
flange required by paragraph (g) of this AD, if those actions were
performed before May 12, 1997 (the effective date of AD 97-07-14)
using Airbus Service Bulletin A320-57-1013, dated April 12, 1989.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International

Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>. Information may be
emailed to<EMAIL_ADDRESS>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. The
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
    (3) Required for Compliance (RC): Except as required by
paragraph (j) of this AD, if the service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures and tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in a serviceable condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0053, dated March 7, 2014,
for related information. This MCAI may be found in the AD docket on
the Internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2015-0926.
    (2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email<EMAIL_ADDRESS>Internet http://www.airbus.com. You may view this 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<PHONE_NUMBER>.

    Issued in Renton, Washington, on April 6, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-09549 Filed 4-23-15; 8:45 am]
 BILLING CODE 4910-13-P