[Federal Register Volume 77, Number 162 (Tuesday, August 21, 2012)]
[Proposed Rules]
[Pages 50407-50411]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-20470]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0855; Directorate Identifier 2011-NM-136-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to all The Boeing Company Model 737-100, -200, -200C,
-300, -400, and -500 series airplanes. The existing AD currently
requires repetitive inspections to detect cracking of the lower corners
of the door frame and cross beam of the forward cargo door, and
corrective actions if necessary. The existing AD also requires eventual
modification of the outboard radius of the lower corners of the door
frame and reinforcement of the cross beam of the forward cargo door,
which would constitute terminating action for the existing repetitive
inspections. Since we issued that AD, we have received additional
reports of fatigue cracking in the radius of the lower frames and in
the lower number 5 cross beam of the forward cargo door. This proposed
AD would revise the compliance times for the preventive modification;
add certain inspections for cracks in the number 5 cross beam of the
forward cargo door; and add inspections of the number 4 cross beam if
cracks are found in the number 5 cross beam, and corrective actions if
necessary. For certain airplanes, this proposed AD would also add a
one-time inspection for airplanes previously modified or repaired, and
a one-time inspection of the reinforcement angle for excessive shimming
or fastener pull-up, and corrective actions if necessary. We are
proposing this AD to prevent fatigue cracking of the lower corners of
the door frame and number 5 cross beam of the forward cargo door, which
could result in rapid depressurization of the airplane.
DATES: We must receive comments on this proposed AD by October 5, 2012.
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, Washington 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.
[[Page 50408]]
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.
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: (425) 917-
6450; fax: (425) 917-6590; email: alan.pohl@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-2012-0855;
Directorate Identifier 2011-NM-136-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On March 31, 2000, we issued AD 2000-07-06, Amendment 39-11660 (65
FR 19302, April 11, 2000), for Model 737-100, -200, -200C, -300, -400,
and -500 series airplanes. That AD requires repetitive inspections to
detect cracking of the lower corners of the door frame and cross beam
of the forward cargo door, and corrective actions, if necessary. That
AD also requires eventual modification of the outboard radius of the
lower corners of the door frame and reinforcement of the cross beam of
the forward cargo door, which would constitute terminating action for
the repetitive inspections. That AD resulted from reports indicating
that fatigue cracks were detected in the lower corners of the door
frame and cross beam of the forward cargo door. We issued that AD to
prevent fatigue cracking of the lower corners of the door frame and
cross beam of the forward cargo door, which could result in rapid
depressurization of the airplane.
Actions Since AD 2000-07-06, Amendment 39-11660 (65 FR 19302, April 11,
2000) Was Issued
Since we issued AD 2000-07-06, Amendment 39-11660 (65 FR 19302,
April 11, 2000), we have received additional reports of fatigue
cracking in the radius of the lower frames and in the Web of the number
5 lower cross beam of the forward cargo door. One report was of a rapid
loss of cabin pressure during descent, as a result of a door crack.
Other reports indicated improper nesting when installing the aft
reinforcement angle during accomplishment of the modification specified
in Boeing Service Bulletin 737-52-1100, Revision 2, dated March 31,
1994; and Boeing Alert Service Bulletin 737-52A1100, Revision 3, dated
July 20, 2000.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 737-52A1100, Revision 5,
dated February 14, 2011; and Boeing Special Attention Service Bulletin
737-52-1149, dated December 11, 2003. For information on the procedures
and compliance times, see this service information at http://www.regulations.gov.
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 these same type
designs.
Proposed AD Requirements
This proposed AD would retain all of the requirements of AD 2000-
07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000). 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.''
Related investigative actions include inspecting the number 4 cross
beam on the forward cargo door for cracking if cracking is found on the
number 5 cross beam, a one-time high frequency eddy current inspection
for cracking of the lower corner frame, and a one-time inspection of
the reinforcement angle. Corrective actions include the following:
Installing a preventive modification, replacing the frame and repairing
any cracking, repairing or replacing the number 5 cross beam, and
replacing the reinforcement angle.
Explanation of Changes Made to Existing Requirements
The compliance times required by AD 2000-07-06, Amendment 39-11660
(65 FR 19302, April 11, 2000), are specified in flight cycles on the
airplane. However, the compliance times in the new actions specified in
the revised service information are specified in door flight cycles,
which are flight cycles accumulated on the forward cargo doors. These
doors are interchangeable between airplanes and they are often
interchanged. Since the unsafe condition stems from the total flight
cycles accumulated on the door and not on the airplane itself, this
proposed AD will specify door flight cycles for the new compliance
times.
We have changed all references to a ``detailed visual inspection''
in the retained requirements of the existing AD to a ``detailed
inspection'' in this proposed AD.
Boeing Commercial Airplanes has received an ODA. We have revised
the retained requirements of the existing AD to delegate the authority
to approve an alternative method of compliance for any repair required
by this proposed AD to the Boeing Commercial Airplanes ODA rather than
a Designated Engineering Representative (DER).
We have included Note 2 of the restated requirements of AD 2000-07-
06, Amendment 39-11660 (65 FR 19302, April 11, 2000), in paragraph (h)
of this proposed AD. Note 3 of the restated requirements of AD 2000-07-
06 is no longer applicable and has been removed from this proposed AD.
These changes do not add any additional burden on the public with
regard to the restated requirements of the existing AD.
We have added Boeing Alert Service Bulletin 737-52A1100, Revision
5, dated February 14, 2011, to paragraph (i)(2) of this AD as the
source of service information for accomplishing the preventive
modification and the reinforcement modification.
Differences Between the Proposed AD and the Service Information
Boeing Alert Service Bulletin 737-52A1100, Revision 5, dated
February 14, 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:
[[Page 50409]]
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.
Changes to Existing AD 2000-07-06, Amendment 39-11660 (65 FR 19302,
April 11, 2000) Format
This proposed AD would retain all requirements of AD 2000-07-06,
Amendment 39-11660 (65 FR 19302, April 11, 2000). Since AD 2000-07-06
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 2000-07-06, Amendment
39[dash]11660 (65 FR 19302, April 11, Corresponding requirement in
2000) this proposed AD
------------------------------------------------------------------------
paragraph (a) paragraph (g)
paragraph (b) paragraph (h)
paragraph (c) paragraph (i)
paragraph (d) paragraph (j)
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Explanation of Change to Costs of Compliance
Since issuance of AD 2000-07-06, Amendment 39-11660 (65 FR 19302,
April 11, 2000), we have increased the labor rate used in the Costs of
Compliance from $80 per work-hour to $85 per work-hour. The Costs of
Compliance information, below, reflects this increase in the specified
labor rate.
Costs of Compliance
We estimate that this proposed AD affects 581 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Action Labor cost Parts cost Cost per product Cost on U.S. operators
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Inspections retained from AD 2000-07- 1 work-hour x $85 per $0 $85 per inspection cycle $49,385 per inspection cycle.
06, Amendment 39[dash]11660 (65 FR hour = $85 per
19302, April 11, 2000). inspection cycle.
Modification retained from AD 2000-07- 18 work-hours x $85 per $1,865 $3,395.................. $1,972,495.
06. hour = $1,530.
Inspections, new proposed action..... 9 work-hours x $85 per $0 $765.................... $444,465.
hour = $765.
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We estimate the following costs to do any necessary modifications
that would be required based on the results of the proposed
inspections. We have no way of determining the number of aircraft that
might need these modifications:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Modification.............................. 84 work-hours x $85 per hour = $12,395 $19,535
$7,140.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs/replacements 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
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD)
[[Page 50410]]
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2012-0855; Directorate Identifier
2011-NM-136-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by October 5,
2012.
(b) Affected ADs
This AD supersedes AD 2000-07-06, Amendment 39-11660 (65 FR
19302, April 11, 2000).
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -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 additional reports of fatigue cracking
in the radius of the lower frames and in the lower number 5 cross
beam of the forward cargo door. We are issuing this AD to prevent
fatigue cracking of the lower corners of the door frame and number 5
cross beam of the forward 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) Retained High Frequency Eddy Current (HFEC) Initial/Repetitive
Inspections
This paragraph restates the requirements of paragraph (a) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), with
revised service information. Within 1 year or 4,500 flight cycles
after May 16, 2000 (the effective date of AD 2000-07-06), whichever
occurs later, perform an HFEC inspection to detect cracking of the
lower corners (forward and aft) of the door frame of the forward
cargo door, in accordance with Boeing 737 Nondestructive Test (NDT)
Manual, D6-37239, Part 6, Section 51-00-00, Figure 4, dated August
5, 1997, or April 5, 2007, or Figure 23, dated August 5, 1997 or
April 5, 2004, as applicable.
(1) If no cracking is detected, repeat the HFEC inspection
thereafter at intervals not to exceed 4,500 flight cycles, until the
requirements of paragraph (i) of this AD have been accomplished.
(2) If any cracking is detected during any inspection required
by paragraph (g) of this AD, prior to further flight, accomplish the
requirements of paragraphs (g)(2)(i) and (g)(2)(ii) of this AD,
which constitute terminating action for the repetitive inspections
required by paragraph (g)(1) of this AD.
(i) Accomplish the requirements of paragraph (g)(2)(i)(A) or
(g)(2)(i)(B) of this AD, and install a cross beam repair and
reinforcement modification of the cross beam, in accordance with
Boeing Service Bulletin 737-52-1100, Revision 2, dated March 31,
1994.
(A) Repair the door frame of the forward cargo door in
accordance with a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA, Transport Airplane Directorate; or
in accordance with data meeting the type certification basis of the
airplane approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make such findings. For a repair or
modification method to be approved by the Manager, Seattle ACO, as
required by this paragraph, and paragraphs (g)(2)(ii), (h)(2),
(h)(3)(ii), and (i)(2) of this AD, the Manager's approval letter
must specifically reference this AD.
(B) Replace the door frame of the forward cargo door with a new
door frame, in accordance with Boeing Service Bulletin 737-52-1100,
Revision 2, dated March 31, 1994.
(ii) Modify the repaired or replaced door frame of the forward
cargo door, in accordance with a method approved by the Manager,
Seattle ACO, or in accordance with data meeting the type
certification basis of the airplane approved by the Boeing
Commercial Airplanes ODA that has been authorized by the Manager,
Seattle ACO, to make those findings.
Note 1 to paragraphs (g), (h), (i), and (j) of this AD:
Accomplishment of Boeing Service Bulletin 737-52-1100, Revision 2,
dated March 31, 1994, does not supersede the requirements of AD 90-
06-02, Amendment 39-6489 (55 FR 8372, March 7, 1990).
(h) Retained Initial Detailed Inspection and Repetitive Inspections
This paragraph restates the requirements of paragraph (b) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000). Within
1 year or 4,500 flight cycles after May 16, 2000 (the effective date
of AD 2000-07-06), whichever occurs later, perform a detailed
inspection to detect cracking of the cross beam (i.e., upper and
lower chord and Web sections) of the forward cargo door, in
accordance with Boeing Service Bulletin 737-52-1100, Revision 2,
dated March 31, 1994. 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.''
(1) If no cracking is detected, repeat the inspection thereafter
at intervals not to exceed 4,500 flight cycles until the
requirements of paragraph (i) of this AD have been accomplished.
(2) If any cracking is detected on the lower chord section of
the cross beam during any inspection required by paragraph (h) of
this AD, prior to further flight, repair in accordance with a method
approved by the Manager, Seattle ACO, or in accordance with data
meeting the type certification basis of the airplane approved by the
Boeing Commercial Airplanes ODA that has been authorized by the
Manager, Seattle ACO, to make those findings.
(3) If any cracking is detected on any area excluding the lower
chord section of the cross beam (i.e., upper chord and Web section)
during any inspection required by paragraph (h) of this AD, prior to
further flight, accomplish the requirements of paragraph (h)(3)(i)
or (h)(3)(ii) of this AD, as applicable, which constitutes
terminating action for the repetitive inspections required by
paragraph (h)(1) of this AD.
(i) For airplanes with line numbers 1 through 1231: Install a
cross beam repair and preventative modification of the outboard
radius of the lower corners (forward and aft) of the door frame, in
accordance with Boeing Service Bulletin 737-52-1100, Revision 2,
dated March 31, 1994.
(ii) For airplanes with line numbers 1232 and subsequent:
Install a cross beam repair and preventative modification of the
outboard radius of the lower corners (forward and aft) of the door
frame, in accordance with a method approved by the Manager, Seattle
ACO, or in accordance with data meeting the type certification basis
of the airplane approved by the Boeing Commercial Airplanes ODA that
has been authorized by the Manager, Seattle ACO, to make those
findings.
(i) Retained Terminating Action
This paragraph restates the requirements of paragraph (c) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), with
revised service information. Within 4 years or 12,000 flight cycles
after May 16, 2000 (the effective date of AD 2000-07-06), whichever
occurs later: Install the preventative modification of the outboard
radius of the lower corners (forward and aft) of the door frame and
the reinforcement modification of the cross beam of the forward
cargo door, in accordance with paragraph (i)(1) or (i)(2) of this
AD, as applicable. Accomplishment of paragraph (i)(1) or (i)(2) of
this AD, as applicable, constitutes terminating action for the
repetitive inspections required by paragraphs (g)(1) and (h)(1) of
this AD.
(1) For airplanes with line numbers 1 through 1231: Accomplish
the preventative modification and the reinforcement modification, in
accordance with Boeing Service Bulletin 737-52-1100, Revision 2,
dated March 31, 1994.
(2) For airplanes with line numbers 1232 and subsequent:
Accomplish the preventative modification and the reinforcement
modification, in accordance with a method approved by the Manager,
Seattle ACO, or in accordance with data meeting the type
certification basis of the airplane approved by the Boeing
Commercial Airplanes ODA that has been authorized by the Manager,
Seattle ACO, to make those findings; or in accordance with Boeing
Alert Service Bulletin 737-52A1100, Revision 5, dated February 14,
2011. As of the effective date of this AD, use only Boeing Alert
Service Bulletin 737-52A1100, Revision 5, dated
[[Page 50411]]
February 14, 2011, to accomplish the modifications required by this
paragraph.
(j) Retained Action for Airplanes on Which Modifications Were
Accomplished Previously
This paragraph restates the requirements of paragraph (d) of AD
2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000). For
all airplanes on which modifications of the forward lower corner of
the door frame and the cross beam of the forward cargo door were
accomplished in accordance with Boeing Service Bulletin 737-52-1100,
dated August 25, 1988, or Revision 1, dated July 20, 1989; or in
accordance with the requirements of AD 90-06-02, Amendment 39-6489
(55 FR 8372, March 7, 1990): Within 4 years or 12,000 flight cycles
after May 16, 2000 (the effective date of AD 2000-07-06), whichever
occurs later, install the reinforcement modification of the aft
corner of the door frame of the forward cargo door, in accordance
with Boeing Service Bulletin 737-52-1100, Revision 2, dated March
31, 1994. Accomplishment of such modification constitutes
terminating action for the repetitive inspections required by
paragraphs (g)(1) and (h)(1) of this AD.
(k) New Inspections and Corrective Actions
Except as provided by paragraphs (m)(1) and (m)(2) of this AD:
At the applicable time specified in paragraph 1.E, ``Compliance,''
of Boeing Alert Service Bulletin 737-52A1100, Revision 5, dated
February 14, 2011, do the inspections required by paragraphs (k)(1)
and (k)(2) of this AD, as applicable. Do all applicable related
investigative and corrective actions before further flight, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1100, Revision 5, dated February 14, 2011;
except as required by paragraph (m)(3) of this AD. Accomplishment of
the inspections required by paragraph (k) of this AD terminates the
requirements of the repetitive inspections required by paragraphs
(g)(1) and (h)(1) of this AD. If any cracking is found in the number
4 cross beam, before further flight, repair in accordance with
Boeing Special Attention Service Bulletin 737-52-1149, dated
December 11, 2003.
Note 2 to paragraph (k) of this AD: Boeing Alert Service
Bulletin 737-52A1100, Revision 5, dated February 14, 2011, refers to
Boeing Special Attention Service Bulletin 737-52-1149, dated
December 11, 2003, as an additional source of guidance for the
inspection for cracks of the number 4 cross beam.
(1) For airplanes identified in Tables 1 and 2 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011: Do a one-time HFEC inspection
of the applicable location for cracks, in accordance with the Work
Instructions, Part I, of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011.
(2) For airplanes identified in Table 3 of paragraph 1.E,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011: Do a one-time general visual
inspection of the reinforcement angle for excessive shimming or
fastener pull-up, in accordance with the Work Instructions, Part
III, of Boeing Alert Service Bulletin 737-52A1100, Revision 5, dated
February 14, 2011.
(l) No Supplemental Structural Inspections Required by This AD
(1) The supplemental structural inspections specified in Table 4
of paragraph 1.E., ``Compliance,'' and Part 5 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-52A1100, Revision
5, dated February 14, 2011, are not required by this AD.
(2) The supplemental structural inspections specified in Table 4
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1100, Revision 5, dated February 14, 2011, may be used in
support of compliance with section 121.1109(c)(2) or 129.109(c)(2)
of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR
129.109(c)(2)). The corresponding actions specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1100, Revision 5, dated February 14, 2011, are not required by
this AD.
(m) Exceptions to Certain Service Information
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-52A1100, Revision 5, dated February 14, 2011,
specifies a compliance time relative to the Revision 5 issue date of
the service bulletin, this AD requires compliance within the
specified compliance time after the effective date of this AD.
(2) Where Table 1, ``Condition'' column of Paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1100,
Revision 5, dated February 14, 2011, specifies ``airplanes without
either the repair or modification accomplished in accordance with
previous releases of this service bulletin,'' the corresponding
condition in this AD is for ``airplanes on which either a repair or
modification was not accomplished before the effective date of this
AD.''
(3) Where Boeing Alert Service Bulletin 737-52A1100, Revision 5,
dated February 14, 2011, specifies to contact Boeing for certain
actions: Before further flight, do the repair using a method
approved in accordance with the procedures specified in paragraph
(n)(1) of this AD.
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, 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 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 2000-07-06,
Amendment 39-11660 (65 FR 19302, April 11, 2000), are approved as
AMOCs for the corresponding requirements of this AD.
(o) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone (425)
917-6450; fax (425) 917-6590; email alan.pohl@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, Washington 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.
Issued in Renton, Washington, on August 13, 2012.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-20470 Filed 8-20-12; 8:45 am]
BILLING CODE 4910-13-P