```

[Federal Register Volume 78, Number 127 (Tuesday, July 2, 2013)]
[Proposed Rules]
[Pages 39633-39637]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-15694]

=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0541; Directorate Identifier 2011-NM-097-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede three existing airworthiness 
directives (ADs) that apply to The Boeing Company Model 757-200, -
200PF, and -200CB series airplanes. The existing ADs currently require 
repetitive inspections and audible tap tests of the upper and lower 
skins of the trailing edge wedges on certain slats, and related 
investigative and corrective actions if necessary. Since we issued 
these ADs, we have received reports of slats disbonding on airplanes on 
which the terminating actions of the existing ADs were completed and 
also reports of slats disbonding on airplanes outside of the 
applicability of the existing ADs. This proposed AD would require a 
determination of the type of trailing edge wedges of the leading edge 
slats, repetitive inspections on certain trailing edge wedges for areas 
of skin-to-core disbonding, and corrective actions if necessary. This 
proposed AD would also provide an optional terminating action for the 
repetitive inspections. This AD would revise the applicability of the 
existing ADs to include additional airplanes. We are proposing this AD 
to prevent delamination of the trailing edge wedge of the leading edge 
slats, possible loss of pieces of the trailing edge wedge assembly 
during flight, reduction of the reduced maneuver and stall margins, and 
consequent reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by August 16, 2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, 
extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. 
You may review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at the 
FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

[[Page 39634]]

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

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-2013-0541; 
Directorate Identifier 2011-NM-097-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On October 23, 1990, we issued AD 90-23-06, Amendment 39-6794 (55 
FR 46499, November 5, 1990), for certain Boeing Model 757 series 
airplanes, which requires close visual inspections of the trailing edge 
wedges on the leading edge slats to detect delamination and physical 
damage, and replacement or repair of defective parts if necessary.
    On December 18, 1991, we issued AD 91-22-51, Amendment 39-8129 (57 
FR 781, January 9, 1992), for certain Boeing Model 757 series 
airplanes, which requires repetitive inspections to detect delamination 
of or physical damage to the trailing edge wedges on the leading edge 
wing slats, and repair if necessary.
    On March 22, 2005, we issued AD 2005-07-08, Amendment 39-14032 (70 
FR 16403, March 31, 2005), for certain Boeing Model 757-200 and -200PF 
series airplanes, which requires repetitive inspections and audible tap 
tests of the upper and lower skins of the trailing edge wedges on 
certain slats, and related investigative and corrective actions if 
necessary. This AD also provides an optional terminating action for the 
repetitive inspections and audible tap tests, which consists of 
replacing the trailing edge wedge assemblies with new, improved wedge 
assemblies.
    Those ADs resulted from multiple reports of damage to the leading 
edge slats. We issued those ADs to prevent delamination of the leading 
edge slats, possible loss of pieces of the trailing edge wedge assembly 
during flight, reduction of the reduced maneuver and stall margins, and 
consequent reduced controllability of the airplane.

Actions Since Existing ADs Were Issued

    Since we issued AD 2005-07-08, Amendment 39-14032 (70 FR 16403, 
March 31, 2005), we have received reports of slat disbonding on 
airplanes on which the optional terminating action of AD 2005-07-08 was 
completed, and also reports of slats disbonding on airplanes outside of 
the applicability of the existing ADs. Additionally, the manufacturer 
has developed a new terminating action, which, when accomplished, 
terminates the repetitive inspections of AD 90-23-06, Amendment 39-6794 
(55 FR 46499, November 5, 1990); AD 91-22-51, Amendment 39-8129 (57 FR 
781, January 9, 1992); and AD 2005-07-08.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletin 757-57-0066, 
dated April 5, 2011. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2013-0541.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 90-23-06, 
Amendment 39-6794 (55 FR 46499, November 5, 1990); AD 91-22-51, 
Amendment 39-8129 (57 FR 781, January 9, 1992); and AD 2005-07-08, 
Amendment 39-14032 (70 FR 16403, March 31, 2005). This proposed AD 
would add airplanes to the applicability statement. This proposed AD 
would also require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between the Proposed AD and the Service Information.'' 
Accomplishment of the new initial proposed inspection and applicable 
corrective actions would terminate the existing requirements.
    The phrase ``related investigative actions'' might be used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that: (1) Are related to the primary actions, and (2) are actions that 
further investigate the nature of any condition found. Related 
investigative actions in an AD could include, for example, inspections.
    In addition, the phrase ``corrective actions'' might be used in 
this proposed AD. ``Corrective actions'' are actions that correct or 
address any condition found. Corrective actions in an AD could include, 
for example, repairs.

Change to Existing AD 90-23-06, Amendment 39-6794 (55 FR 46499, 
November 5, 1990)

    This proposed AD would retain all the requirements of AD 90-23-06, 
Amendment 39-6794 (55 FR 46499, November 5, 1990). Since AD 90-23-06 
was issued, the AD format has been revised, and certain paragraphs have 
been rearranged. As a result, the corresponding paragraph identifiers 
have changed in this proposed AD, as listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
    Requirement in AD 90-23-06,
  Amendment 39-6794 (55 FR 46499,     Corresponding requirement in this
         November 5, 1990)                       proposed AD
------------------------------------------------------------------------
 paragraph (A)                       paragraph (g)(1).
 paragraph (B)                       paragraph (g)(2).
 paragraph (C)                       paragraph (g)(3).
 paragraph (D)                       paragraph (h).
------------------------------------------------------------------------

Change to Existing AD 91-22-51, Amendment 39-8129 (57 FR 781, January 
9, 1992)

    The corresponding paragraph identifiers also have been changed for 
AD 91-22-51, Amendment 39-8129 (57 FR 781, January 9, 1992), and are 
listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
    Requirement in AD 91-22-51,
   Amendment 39-8129 (57 FR 781,      Corresponding requirement in this
         January 9, 1992)                        proposed AD
------------------------------------------------------------------------
 paragraph (a)                       paragraph (i)(1).
 paragraph (a)(1)                    paragraph (i)(1)(i).
 paragraph (a)(2)                    paragraph (i)(1)(ii).
 paragraph (b)                       paragraph (i)(2).
 paragraph (c)                       paragraph (j).
------------------------------------------------------------------------

Change to Existing AD 2005-07-08, Amendment 39-14032 (70 FR 16403, 
March 31, 2005)

    This proposed AD also would retain all the requirements of AD 2005-
07-08,

[[Page 39635]]

Amendment 39-14032 (70 FR 16403, March 31, 2005). Since AD 2005-07-08 
was issued, the AD format has been revised, and certain paragraphs have 
been rearranged. As a result, the corresponding paragraph identifiers 
have changed in this proposed AD, as listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
  Requirement in  AD 2005-07-08,
 Amendment 39-14032  (70 FR 16403,    Corresponding requirement in this
          March 31, 2005)                        proposed AD
------------------------------------------------------------------------
 paragraph (f)                       paragraph (k).
 paragraph (g)                       paragraph (l).
 paragraph (h)                       paragraph (m).
 paragraph (i)                       paragraph (n).
 paragraph (j)                       paragraph (o).
------------------------------------------------------------------------

Differences Between the Proposed AD and the Service Information

    Boeing Special Attention Service Bulletin 757-57-0066, dated April 
5, 2011, specifies to contact the manufacturer for instructions on how 
to repair certain conditions, but this proposed AD would require 
repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 640 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection/test [retained actions  6 work-hours x $85               $0  $510 per inspection  $326,400 per
 from existing ADs].                per hour = $510                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
Inspection/test [new proposed      Up to 20 work-hours               0  Up to $1,700 per     Up to $1,088,000
 action].                           x $85 per hour =                     inspection cycle.    per inspection
                                    $1,700 per                                                cycle.
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this 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 that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (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) 
90-23-06, Amendment 39-6794 (55 FR 46499, November 5, 1990); AD 91-22-
51, Amendment 39-8129 (57 FR 781, January 9, 1992); and AD 2005-07-08, 
Amendment 39-14032 (70 FR 16403, March 31, 2005), and adding the 
following new AD:

The Boeing Company: Docket No. FAA-2013-0541; Directorate Identifier 
2011-NM-097-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by August 16, 
2013.

(b) Affected ADs

    This AD supersedes AD 2005-07-08, Amendment 39-14032 (70 FR 
16403, March 31, 2005); AD 91-22-51, Amendment 39-8129 (57 FR 781, 
January 9, 1992); and AD 90-23-06, Amendment 39-6794 (55 FR 46499, 
November 5, 1990).

(c) Applicability

    This AD applies to all The Boeing Company Model 757-200, -200PF, 
and -200CB series airplanes, certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of slat disbonding on airplanes 
that had performed the terminating actions of an AD; and we have 
received reports of slats disbonding on airplanes outside of the 
applicability of the existing ADs. We are issuing this AD to prevent 
delamination of the trailing edge

[[Page 39636]]

wedge of the leading edge slats, possible loss of pieces of the 
trailing edge wedge assembly during flight, reduction of the reduced 
maneuver and stall margins, and consequent reduced controllability 
of the airplane.

(f) Compliance

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

(g) Retained Repetitive Inspections of Trailing Edge Wedges

    This paragraph restates the requirements of paragraphs A., B., 
and C. of AD 90-23-06, Amendment 39-6794 (55 FR 46499, November 5, 
1990).
    (1) For Model 757 series airplanes, line numbers 001 through 
091: Prior to the accumulation of 11,000 flight hours, or within the 
next 10 calendar days after September 21, 1990 (the effective date 
of telegraphic AD T90-20-51), whichever occurs later, perform a 
close detailed visual inspection of the trailing edge wedges on all 
the leading edge slats for delamination and physical damage, in 
accordance with Boeing Alert Service Bulletin 757-57A0038, dated 
September 21, 1990; Boeing Alert Service Bulletin 757-57A0038, 
Revision 1, dated September 25, 1990; or Boeing Alert Service 
Bulletin 757-57A0038, Revision 2, dated October 10, 1990.

    Note 1 to paragraph (g)(1) of this AD:  Telegraphic AD T90-20-51 
was sent directly to owners and operators of the affected airplanes 
on September 21, 1990. AD T90-20-51 was not published in the Federal 
Register, because it was promptly superseded by AD 90-23-06, 
Amendment 39-6794 (55 FR 46499, November 5, 1990).

    (2) For Model 757 series airplanes, line numbers 092 through 
158: Prior to the accumulation of 11,000 flight hours, or within the 
next 10 calendar days after November 19, 1990 (the effective date of 
AD 90-23-06, Amendment 39-6794 (55 FR 46499, November 5, 1990)), 
whichever occurs later, perform a close detailed visual inspection 
of the trailing edge wedges on all the leading edge slats for 
delamination and physical damage, in accordance with Boeing Alert 
Service Bulletin 757-57A0038, dated September 21, 1990; Boeing Alert 
Service Bulletin 757-57A0038, Revision 1, dated September 25, 1990; 
or Boeing Alert Service Bulletin 757-57A0038, Revision 2, dated 
October 10, 1990.
    (3) Repeat the inspections required by paragraph (g)(1) or 
(g)(2) of this AD, as applicable, at intervals not to exceed 300 
flight hours. Doing the initial inspection and applicable corrective 
actions required by paragraph (p) of this AD terminates the 
requirements of paragraph (g) of this AD.

(h) Retained Repair or Replacement for Paragraph (g) of This AD

    This paragraph restates the repair or replacement required by 
paragraph D. of AD 90-23-06, Amendment 39-6794 (55 FR 46499, 
November 5, 1990). If delamination and/or physical damage are found 
during any inspection required by paragraph (g) of this AD, prior to 
further flight, repair using a method approved in accordance with 
the procedures specified in paragraph (u) of this AD or replace with 
new parts. Doing the initial inspection and applicable corrective 
actions required by paragraph (p) of this AD terminates the 
requirements of paragraph (h) of this AD.

(i) Retained Repetitive Inspections for Certain Airplanes

    This paragraph restates the repetitive inspections required by 
paragraphs (a) and (b) of AD 91-22-51, Amendment 39-8129 (57 FR 781, 
January 9, 1992). For Model 757 series airplanes, line numbers 140 
through 335, accomplish the following:
    (1) Perform a close detailed visual inspection of the trailing 
edge wedges of slats 1 through 4 and 7 through 10, for delamination 
and physical damage, in accordance with Boeing Alert Service 
Bulletin 757-57A0045, dated October 16, 1991, at the times specified 
below, until the initial inspection and applicable corrective 
actions required by paragraph (p) of this AD are accomplished.
    (i) For airplanes that have accumulated 5,000 or more flight 
hours as of January 24, 1992 (the effective date AD 91-22-51, 
Amendment 39-8129 (57 FR 781, January 9, 1992)): Within the next 10 
calendar days after January 24, 1992, and thereafter at intervals 
not to exceed 300 flight hours.
    (ii) For airplanes that have accumulated less than 5,000 flight 
hours as of January 24, 1992 (the effective date AD 91-22-51, 
Amendment 39-8129 (57 FR 781, January 9, 1992)): Within the next 300 
flight hours after January 24, 1992, and thereafter at intervals not 
to exceed 300 flight hours.
    (2) Within the next 300 flight hours after January 24, 1992 (the 
effective date of AD 91-22-51, Amendment 39-8129 (57 FR 781, January 
9, 1992), perform a ``coin-tap'' inspection of the trailing edge 
wedges of slats 1 through 4 and 7 through 10 for delamination and 
physical damage, in accordance with Boeing Alert Service Bulletin 
757-57A0045, dated October 16, 1991. Repeat this inspection at 
intervals not to exceed 1,500 flight hours.

(j) Retained Repair or Replacement for Paragraph (i) of This AD

    This paragraph restates the repair or replacement required by 
paragraph (c) of AD 91-22-51, Amendment 39-8129 (57 FR 781, January 
9, 1992). If delamination and/or physical damage are found as a 
result of the inspections required by paragraph (i)(1) or (i)(2) of 
this AD, prior to further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (u) of this AD 
or replace with new parts. If a repair is accomplished or if new 
parts are installed, the inspections required by paragraphs (i)(1) 
and (i)(2) of this AD must be continued. Doing the initial 
inspection and applicable corrective actions in paragraph (p) of 
this AD terminates the requirements of paragraphs (i) and (j) of 
this AD.

(k) Retained Repetitive Inspections and Tests

    This paragraph restates the repetitive inspections and tests 
required by paragraph (f) of AD 2005-07-08, Amendment 39-14032 (70 
FR 16403, March 31, 2005).
    (1) For Model 757-200 and -200PF series airplanes identified in 
Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003: 
Within 18 months after May 5, 2005 (the effective date of AD 2005-
07-08, Amendment 39-14032 (70 FR 16403, March 31, 2005)), do a 
detailed inspection and an audible tap test of the upper and lower 
skins of the trailing edge wedges on slats No. 2 through No. 4 
inclusive and No. 7 through No. 9 inclusive, for evidence of damage 
or cracking, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003. 
Repeat the detailed inspection and audible tap test thereafter at 
intervals not to exceed 18 months. Doing the initial inspection and 
applicable corrective actions in paragraph (p) of this AD terminates 
the requirements of paragraph (k) of this AD.
    (2) For the purposes of this AD, a detailed inspection is: ``An 
intensive examination of a specific item, installation, or assembly 
to detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at an 
intensity deemed appropriate. Inspection aids such as mirror, 
magnifying lenses, etc., may be necessary. Surface cleaning and 
elaborate procedures may be required.''

(l) Retained Related Investigative and Corrective Actions

    This paragraph restates the related investigative and corrective 
actions required by paragraph (g) of AD 2005-07-08, Amendment 39-
14032 (70 FR 16403, March 31, 2005). If any damage or cracking is 
found during any inspection or audible tap test required by 
paragraph (k) of this AD: Before further flight, do the related 
investigative action, if applicable, and replace the affected part 
with a new trailing edge wedge assembly or repair the affected part, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-57A0063, dated June 26, 2003. Accomplishing the 
replacement terminates the repetitive inspections and audible tap 
tests required by paragraph (k) of this AD for that wedge assembly 
only. Doing the initial inspection and applicable corrective actions 
in paragraph (p) of this AD terminates the requirements of paragraph 
(l) of this AD.

(m) Retained Credit for Previous Actions

    This paragraph restates the credit for actions accomplished 
previously as specified in paragraph (h) of AD 2005-07-08, Amendment 
39-14032 (70 FR 16403, March 31, 2005). This paragraph provides 
credit for the actions required by paragraph (k) of this AD, if 
those actions were performed before May 5, 2005 (the effective date 
of AD 2005-07-08, Amendment 39-14032 (70 FR 16403, March 31, 2005)) 
using all of the actions specified in the Accomplishment 
Instructions of Boeing Service Bulletin 757-57A0038, Revision 5, 
dated July 16, 1992; or Boeing Service Bulletin 757-57A0038, 
Revision 6, dated November 10, 1994; in conjunction with the use of 
BMS 5-137 adhesive.

(n) Retained Parts Installation Limitations

    This paragraph restates the parts installation limitation of 
paragraph (i) of AD

[[Page 39637]]

2005-07-08, Amendment 39-14032 (70 FR 16403, March 31, 2005), with 
new actions. For Model 757-200 and -200PF series airplanes 
identified in Boeing Alert Service Bulletin 757-57A0063, dated June 
26, 2003: As of May 5, 2005 (the effective date of AD 2005-07-08), 
no trailing edge wedge assembly having a part number listed in the 
``Existing Part Number'' column of the table in paragraph 2.C.3. of 
Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003, may 
be installed on any airplane, unless it has been inspected, tested, 
and had any necessary corrective actions accomplished in accordance 
with paragraphs (k) and (l) of this AD or in accordance with 
paragraphs (p) and (q) of this AD. As of the effective date of this 
AD, no part identified in this paragraph may be installed on any 
airplane unless it has been inspected, tested, and had all 
applicable corrective actions accomplished in accordance with 
paragraphs (p) and (q) of this AD.

(o) Retained Optional Terminating Action

    This paragraph restates the optional terminating action 
previously specified in paragraph (j) of AD 2005-07-08, Amendment 
39-14032 (70 FR 16403, March 31, 2005). Replacing all trailing edge 
wedge assemblies with new, improved wedge assemblies (type B) in 
accordance with Part III of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003, 
terminates the requirements of paragraph (k) of this AD.

(p) New Inspection To Determine Slat Wedge Type

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 757-57-
0066, dated April 5, 2011, except as specified in paragraph (s) of 
this AD: Do an inspection of the trailing edge wedges of the leading 
edge slats, or a review of airplane maintenance records, to 
determine whether each slat wedge is a type A or a type B, in 
accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 757-57-0066, dated April 5, 2011.

(q) New Type A Slat Wedge Repetitive Inspections and Corrective Actions

    For each type A trailing edge slat wedge found during the 
inspection or records review required by paragraph (p) of this AD: 
At the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Boeing Special Attention Service Bulletin 757-57-0066, dated 
April 5, 2011, except as specified in paragraph (s) of this AD, do 
an ultrasonic or tap test inspection for disbonds of each leading 
edge slat trailing edge wedge, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 757-57-
0066, dated April 5, 2011. Repeat the inspection thereafter at 
intervals not to exceed 3,000 flight cycles or 24 months, whichever 
occurs first.
    (1) For any disbond found during any inspection required by 
paragraph (q) of this AD that is less than or equal to 1.50 inches 
in maximum dimension, and is located more than or equal to 1.0 inch 
from the edge of the panel, and is located more than or equal to 4 
times the disbond maximum dimension, measured edge to edge, from 
adjacent damage: Within 600 flight cycles after the disbond was 
found, do the inspection required by paragraph (q) of this AD of the 
disbond area, in accordance with the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 757-57-0066, dated April 
5, 2011. Repeat the inspection thereafter at intervals not to exceed 
600 flight cycles. Within 3,000 flight cycles after the disbond was 
found: Repair the disbond, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 757-57-
0066, dated April 5, 2011: or replace the affected trailing edge 
slat wedge using a method approved in accordance with the procedures 
specified in paragraph (u) of this AD.
    (2) For any disbond found during any inspection required by 
paragraph (q) of this AD that is more than 1.50 inches in maximum 
dimension, or is located less than 1.0 inch from the edge of the 
panel, or is located less than 4 times the disbond maximum 
dimension, measured edge to edge, from adjacent damage: Before 
further flight, repair or replace using a method approved in 
accordance with the procedures specified in paragraph (u) of this 
AD.

(r) Repetitive Inspections of Certain Replaced or Repaired Wedges

    (1) For any trailing edge slat wedge that is replaced with a 
type A wedge: Within 3,000 flight cycles after the replacement or 
within 24 months after the replacement, whichever occurs first, do 
the actions required by paragraph (q) of this AD on the replaced 
type A trailing edge slat wedge. Repeat the inspection thereafter at 
intervals not to exceed 3,000 flight cycles or 24 months, whichever 
occurs first.
    (2) For any trailing edge type A slat wedge that is repaired: 
Within 600 flight cycles after the repair, do the actions required 
by paragraph (q) of this AD on the repaired area. Repeat the 
inspection thereafter at intervals not to exceed 600 flight cycles.

 (s) Exception to Compliance Time

    Where Paragraph 1.E., ``Compliance,'' of Boeing Special 
Attention Service Bulletin 757-57-0066, dated April 5, 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''.

(t) New Terminating Actions

    (1) Doing the initial inspection specified in paragraph (q) of 
this AD and applicable type A trailing edge slat wedge repair or 
replacement, in accordance with the actions specified in paragraph 
(q)(1) or (q)(2) of this AD, terminates the requirements of 
paragraphs (g), (h), (i), (j), (k), and (l) of this AD.
    (2) Replacing a type A wedge with a type B wedge using a method 
approved in accordance with the procedures specified in paragraph 
(u) of this AD terminates the repetitive inspections of a type A 
trailing edge slat wedge of the leading edge required by paragraph 
(q) of this AD.

(u) 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: 9-ANM-Seattle-ACO-AMOC-Requests-faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes 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 the ADs 
specified in paragraphs (u)(4)(i), (u)(4)(ii), and (u)(4)(iii) of 
this AD are approved as AMOCs for the corresponding provisions of 
this AD.
    (i) AD 90-23-06, Amendment 39-6794 (55 FR 46499, November 5, 
1990).
    (ii) AD 91-22-51, Amendment 39-8129 (57 FR 781, January 9, 
1992).
    (iii) AD 2005-07-08, Amendment 39-14032 (70 FR 16403, March 31, 
2005).

(v) Related Information

    (1) For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft 
Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6440; fax: 425-917-6590; email: 
Nancy.Marsh@faa.gov.
    (2) 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; phone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on June 14, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-15694 Filed 7-1-13; 8:45 am]
BILLING CODE 4910-13-P
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