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