[Federal Register Volume 77, Number 233 (Tuesday, December 4, 2012)]
[Proposed Rules]
[Pages 71723-71729]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-29170]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 77, No. 233 / Tuesday, December 4, 2012 /
Proposed Rules
[[Page 71723]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1156; Directorate Identifier 2011-NM-205-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 an existing airworthiness directive
(AD) that applies to certain The Boeing Company Model 737-200, -200C, -
300, and -400 series airplanes. The existing AD currently requires
repetitive inspections to detect cracking of the corners of the door
frame and the cross beams of the aft cargo door, and corrective actions
if necessary. The existing AD also requires a modification to the aft
cargo door, which terminates the repetitive inspections. Since we
issued that AD, we have received reports of cracking on doors on
airplanes that were not included in the existing AD. This proposed AD
would add airplanes to the applicability, add inspections and related
investigative and corrective actions, and revise certain inspection
types. This proposed AD would also reduce the compliance time, for
certain doors, to do a modification of the doors. We are proposing this
AD to prevent fatigue cracking of the corners of the door frame and the
cross beams of the aft cargo door, which could result in rapid
depressurization of the airplane.
DATES: We must receive comments on this proposed AD by January 18,
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 proposed 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 98057-3356. 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.
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: [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-2012-1156;
Directorate Identifier 2011-NM-205-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 July 2, 2001, we issued AD 2000-06-13 R1, Amendment 39-12317 (66
FR 36146, July 11, 2001), for certain The Boeing Company Model 737-200,
-200C, -300, and -400 series airplanes. That AD requires repetitive
inspections to detect cracking of the corners of the door frame and the
cross beams of the aft cargo door, and corrective actions, if
necessary. That AD also requires a modification to the aft cargo door,
which terminates the repetitive inspections. That AD resulted from
reports of cracking in the forward and aft corner frame of the aft
cargo door and in the lower cross beam. We issued that AD to prevent
fatigue cracking of the corners of the door frame and the cross beams
of the aft cargo door, which could result in rapid depressurization of
the airplane.
Actions Since Existing AD 2000-06-13 R1, Amendment 39-12317 (66 FR
36146, July 11, 2001) Was Issued
Since we issued AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146,
July 11, 2001), we received reports of cracking on doors on airplanes
that were not included in the existing AD. Therefore, we have
determined that the applicability of AD 2000-06-13 R1 must be expanded
to include all The Boeing Company Model 737-200, -200C, -300, -400, and
-500 series airplanes in order to adequately address the identified
unsafe condition. The existing AD also bases compliance times and
repetitive intervals on airplane flight cycles. Since that AD was
issued, we have determined that door interchangeability has a
significant impact on addressing the unsafe condition. Doors may be
rotated from airplane to airplane, and a door may have accumulated
considerably more cycles than the
[[Page 71724]]
airplane on which it is installed. Therefore, this proposed AD bases
compliance times and repetitive intervals on door flight cycles.
In addition, more work is necessary on airplanes that have not
accomplished the repair or preventive modification specified in Boeing
Alert Service Bulletin 737-52A1079, Revision 6, dated November 18,
1999, or previous issues of that service bulletin. We have also
determined that the compliance time to do a modification of those doors
should be reduced. We referred to Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999, as the appropriate source
of service information for accomplishing the required actions specified
in AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001).
We have also determined that additional work is necessary on airplanes
on which certain repairs and modifications specified in Boeing Alert
Service Bulletin 737-52A1079, Revision 6, dated November 18, 1999, or
previous issues of that service bulletin, have been done.
Relevant Service Information
We reviewed the following service information:
Boeing Alert Service Bulletin 737-52A1153, dated July 13,
2011.
Boeing Alert Service Bulletin 737-52A1079, Revision 7,
dated December 17, 2010.
Boeing Special Attention Service Bulletin 737-52-1154,
dated December 17, 2010.
For information on the procedures and compliance times, see this
service information at http://www.regulations.gov by searching for
Docket No. FAA-2012-1156.
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 the requirements of AD 2000-06-13
R1, Amendment 39-12317 (66 FR 36146, July 11, 2001). This proposed AD
would add airplanes to the applicability. 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.''
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 action, 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 Requirements
Since AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11,
2001), 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 existing AD 2000-
06-13 R1, Amendment 39[dash]12317 Corresponding requirement in this
(66 FR 36146, July 11, 2001) proposed AD
------------------------------------------------------------------------
paragraph (a).................... paragraph (h)
paragraph (b).................... paragraph (i)
paragraph (c).................... paragraph (j)
paragraph (d).................... paragraph (k)
paragraph (e).................... paragraph (l)
------------------------------------------------------------------------
We have revised the retained paragraph (d) of AD 2000-06-13 R1,
Amendment 39-12317 (66 FR 36146, July 11, 2001) (which corresponds to
paragraph (k) of this proposed AD), by removing reference to Boeing 737
Nondestructive Test Manual, Part 6, Chapter 51-00-00 (Figure 4 or
Figure 23) for the high frequency eddy current inspection. Instead, we
have added Note 1 to paragraph (k) of this proposed AD to specify that
guidance on the inspection can be found in Boeing 737 Nondestructive
Test Manual, Part 6, Chapter 51-00-00 (Figure 4 or Figure 23).
We have also moved the method of compliance specified in Note 3 of
AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001), into
paragraph (m) of this proposed AD.
We have also revised the language for the credit for previous
service information specified in Note 4 of AD 2000-06-13 R1, Amendment
39-12317 (66 FR 36146, July 11, 2001), and included it in paragraph (n)
of this proposed AD.
Differences Between the Proposed AD and the Service Information
Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated
December 17, 2010; and Boeing Special Attention Service Bulletin 737
52-1154, dated December 17, 2010; specify 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.
Table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-52A1079, Revision 7, dated December 17, 2010, references
an incorrect part number for reinforcement angles. Paragraph (q) of
this proposed AD specifies the correct part number.
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011; and
Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated December
17, 2010; specify accomplishing supplemental structural inspections.
Those inspections are not required by this proposed AD. The damage
tolerance inspections specified in those service bulletins may be used
in support of compliance with section 121.1109(c)(2) or 129.109(b)(2)
of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR
129.109(b)(2)).
Clarification of Line Numbers
For certain actions, Boeing Alert Service Bulletin 737-52A1079,
Revision
[[Page 71725]]
7, dated December 17, 2010, specifies line numbers 6 through 873
inclusive, but the corresponding action in Boeing Alert Service
Bulletin 737-52A1153, dated July 13, 2011, specifies line numbers prior
to 874. Airplanes having line numbers 1 through 5 are out of service;
therefore, those airplanes are not subject to the requirements of this
proposed AD.
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
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of airplanes of
Action Labor cost Parts cost Cost per product U.S. Registry Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed inspection [retained 2 work-hours x $85 per $0 $170 per inspection 494 $83,890 per inspection
action from existing AD 2000-06-13 hour = $170 per cycle. cycle.
R1, Amendment 39[dash]12317 (66 FR inspection cycle.
36146, July 11, 2001)].
High frequency eddy current 4 work-hours x $85 per $0 $340 per inspection 494 $167,960 per
inspection [retained action from hour = $340 per cycle. inspection cycle.
existing AD 2000-06-13 R1, inspection cycle.
Amendment 39[dash]12317 (66 FR
36146, July 11, 2001)].
Modification [retained action from 144 work-hours x $85 $5,430 $17,670.............. 494 $8,728,980
existing AD 2000-06-13 R1, per hour = $12,240.
Amendment 39[dash]12317 (66 FR
36146, July 11, 2001)].
Determination of door configuration 1 work-hour x $85 per $0 $85.................. 581 $49,385
[new proposed action]. hour = $85.
Inspections [new proposed action].. 6 work-hours x $85 per $0 $510 per inspection 581 $296,310 per
hour = $510 per cycle. inspection cycle.
inspection cycle.
Modification [new proposed action]. 59 work-hours x $85 $30,536 $35,551.............. (1) Unknown.
per hour = $5,015.
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ The number of airplanes that would be required to have this modification accomplished is dependent on no cracking being found during a certain
inspection.
We estimate the following costs to do any necessary related
investigative and corrective actions that would be required based on
the results of the proposed inspections. We have no way of determining
the number of aircraft that might need these actions:
On-Condition Costs
------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
------------------------------------------------------------------------
Related investigative and 59 work-hours x $30,536 $35,551
corrective actions. $85 per hour =
$5,015.
------------------------------------------------------------------------
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) 2000-06-13 R1, Amendment 39-12317
[[Page 71726]]
(66 FR 36146, July 11, 2001), and adding the following new AD:
The Boeing Company: Docket No. FAA-2012-1156; Directorate Identifier
2011-NM-205-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by January 18,
2013.
(b) Affected ADs
This AD supersedes AD 2000-06-13 R1, Amendment 39-12317 (66 FR
36146, July 11, 2001), which revised AD 2000-06-13, Amendment 39-
11654 (65 FR 17583, April 4, 2000). AD 2000-06-13 superseded AD 98-
25-06, Amendment 39-10931 (63 FR 67769, December 9, 1998).
(c) Applicability
This AD applies to all The Boeing Company Model 737-200, -200C,
-300, -400, and -500 series airplanes, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 52, Doors.
(e) Unsafe Condition
This AD was prompted by reports of cracking in the forward and
aft corner frame of the aft cargo door and in the lower cross beam.
We are issuing this AD to prevent fatigue cracking of the corners of
the door frame and the cross beams of the aft cargo door, which
could result in rapid depressurization of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Affected Airplanes for Retained Paragraphs
Paragraphs (h), (i), (j), (k), and (l) of this AD are restated
from AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11,
2001). These paragraphs apply to Model 737-200 and -200C series
airplanes, line numbers 6 through 873 inclusive; and Model 737-200,
-200C, -300, and -400 series airplanes, line numbers 874 through
1642 inclusive; equipped with an aft cargo door having Boeing part
number (P/N) 65-47952-1 or P/N 65-47952-524, excluding airplanes
identified in paragraphs (g)(1) and (g)(2) of this AD.
(1) Those airplanes on which that door has been modified as
specified in Boeing Service Bulletin 737-52-1079. Or,
(2) Those airplanes on which the door assembly having P/N 65-
47952-524 includes four straps (P/Ns 65-47952-139, 65-47952-140, 65-
47952-141, and 65-47952-142) and a thicker lower cross beam web (P/N
65-47952-157).
(h) Retained Inspections and Corrective Actions
This paragraph restates the actions required by paragraph (a) of
AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001),
with revised service information. For airplanes identified in
paragraph (g) of this AD: Within 90 days or 700 flight cycles after
December 24, 1998 (the effective date of AD 98-25-06, Amendment 39-
10931 (63 FR 67769, December 9, 1998)), whichever occurs later,
perform an internal detailed visual inspection to detect cracking of
the corners of the door frame and the cross beams of the aft cargo
door, in accordance with Boeing Service Bulletin 737-52-1079,
Revision 5, dated May 16, 1996; Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Boeing Alert
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
Accomplishment of the modification required by paragraph (l) of this
AD constitutes terminating action for the repetitive inspection
requirements of this paragraph. Doing the inspections required by
paragraph (p) or (s) of this AD terminates the inspections required
by this paragraph.
(1) If no cracking is detected, accomplish the requirements of
either paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
(i) Repeat the internal visual inspection thereafter at
intervals not to exceed 4,500 flight cycles. Or
(ii) Prior to further flight, modify the corners of the door
frame and the cross beams of the aft cargo door, in accordance with
Boeing Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996;
Boeing Alert Service Bulletin 737-52A1079, Revision 6, dated
November 18, 1999; or Boeing Alert Service Bulletin 737-52A1079,
Revision 7, dated December 17, 2010. Accomplishment of such
modification constitutes terminating action for the repetitive
inspection requirements of paragraph (h)(1)(i) of this AD.
(2) If any cracking is detected in the upper or lower cross
beams, prior to further flight, modify the cracked beam, in
accordance with Part I of the Accomplishment Instructions of Boeing
Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996; Part I
of the Accomplishment Instructions of Boeing Alert Service Bulletin
737-52A1079, Revision 6, dated November 18, 1999; or Part II of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Accomplishment of such
modification constitutes terminating action for the repetitive
inspection requirements of paragraph (h)(1)(i) of this AD for the
modified beam.
(3) If any cracking is detected in the forward or aft upper door
frame, prior to further flight, repair the frame and modify the
corners of the door frame of the aft cargo door, in accordance with
Part I of the Accomplishment Instructions of Boeing Service Bulletin
737-52-1079, Revision 5, dated May 16, 1996; Part I of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Part II of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010; except as provided by
paragraph (i) of this AD. Accomplishment of such modification
constitutes terminating action for the repetitive inspection
requirements of paragraph (h)(1)(i) of this AD for the upper door
frame.
(4) If any cracking is detected in the forward or aft lower door
frame, prior to further flight, replace the damaged frame with a new
frame, and modify the corners of the door frame of the aft cargo
door, in accordance with Part I of the Accomplishment Instructions
of Boeing Service Bulletin 737-52-1079, Revision 5, dated May 16,
1996; Part I of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1079, Revision 6, dated November 18, 1999;
or Part II of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
Accomplishment of such modification constitutes terminating action
for the repetitive inspection requirements of paragraph (h)(1)(i) of
this AD for the lower door frame.
(i) Retained Exception for Certain Actions Specified in Paragraphs (h)
and (l) of This AD
This paragraph restates the requirement of paragraph (b) of AD
2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001). For
actions required by paragraphs (h) and (l) of this AD: Where Boeing
Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996; Boeing
Alert Service Bulletin 737-52A1079, Revision 6, dated November 18,
1999; or Boeing Alert Service Bulletin 737-52A1079, Revision 7,
dated December 17, 2010; specifies that certain repairs are to be
accomplished in accordance with instructions received from Boeing,
this AD requires that, prior to further flight, such repairs be
accomplished in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or using a method
approved in accordance with the procedures specified in paragraph
(x) of this AD.
(j) Retained Corrective Actions for Certain Cracking Found During
Inspection Required by Paragraph (h) of This AD
This paragraph restates the corrective action required by
paragraph (c) of AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146,
July 11, 2001), with revised service information. If any cracking of
the outer chord of the upper or lower cross beams of the aft cargo
door is detected during any inspection required by paragraph (h) of
this AD, prior to further flight, accomplish the repair specified in
paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD. For a repair
method to be approved, as required by paragraphs (j)(1), (j)(3), and
(j)(4) of this AD, the approval letter must specifically reference
this AD.
(1) Repair in accordance with a method approved by the Manager,
Seattle ACO.
(2) Repair in accordance with Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Boeing Alert
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
(3) Repair in accordance with data meeting the type
certification basis of the airplane approved by a Boeing Company
Designated Engineering Representative who has been authorized by the
FAA to make such findings.
(4) Repair in accordance with a method approved by the Boeing
Commercial Airplanes Organization Designation Authorization (ODA)
whom we have authorized to make those findings.
[[Page 71727]]
(k) Retained Inspections and Corrective Actions for Airplanes
Identified in Paragraph (g) of This AD
This paragraph restates the actions required by paragraph (d) of
AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001),
with revised service information. For airplanes identified in
paragraph (g) of this AD: Within 4,500 flight cycles or 1 year after
May 9, 2000 (the effective date of AD 2000-06-13, amendment 39-11654
(65 FR 17583, April 4, 2000), whichever occurs later, perform a high
frequency eddy current inspection (HFEC) to detect cracking of the
four corners of the door frame of the aft cargo door, using a method
approved in accordance with the procedures specified in paragraph
(x) of this AD, or in accordance with Boeing Alert Service Bulletin
737-52A1079, Revision 6, dated November 18, 1999; or Boeing Alert
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
Accomplishment of the modification required by paragraph (l) of this
AD constitutes terminating action for the repetitive inspection
requirements of this paragraph. Doing the inspections required by
paragraph (p) or (s) of this AD terminates the inspections required
by this paragraph.
Note 1 to paragraph (k) of this AD: Additional guidance for the
inspection can be found in Boeing 737 Nondestructive Test Manual,
Part 6, Chapter 51-00-00 (Figure 4 or Figure 23).
(1) If no cracking of the corners of the door frame of the aft
cargo door is detected, repeat the HFEC inspections thereafter at
intervals not to exceed 4,500 flight cycles until accomplishment of
the modification specified in paragraph (l) of this AD.
(2) If any cracking of the corners of the door frame of the aft
cargo door is detected, prior to further flight, replace the damaged
frame with a new frame, and modify the four corners of the door
frame, in accordance with Part II and Part III of the Accomplishment
Instructions of Boeing Service Bulletin 737-52-1079, Revision 5,
dated May 16, 1996; Part II and Part III of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision
6, dated November 18, 1999; or Part III and Part IV of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Accomplishment of such
modification constitutes terminating action for the repetitive
inspection requirements of paragraph (k)(1) of this AD for that door
frame.
(l) Retained Terminating Action for Inspections Specified in Paragraphs
(h) and (k) of This AD
This paragraph restates the action required by paragraph (e) of
AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001),
with revised service information. For airplanes identified in
paragraph (g) of this AD: Within 4 years or 12,000 flight cycles
after August 15, 2001 (the effective date of AD 2000-06-13 R1),
whichever occurs later, modify the four corners of the door frame
and the cross beams of the aft cargo door, in accordance with Part
II of the Accomplishment Instructions of Boeing Service Bulletin
737-52-1079, Revision 5, dated May 16, 1996; Part II of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Part III of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Accomplishment of that
modification constitutes terminating action for the repetitive
inspection requirements of paragraphs (h) and (k) of this AD.
(m) Retained Method of Compliance
This paragraph restates the method of compliance of Note 3 of AD
2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001).
Accomplishment of the modification required by paragraph (a) of AD
90-06-02, Amendment 39-6489 (55 FR 8372, March 7, 1990), is
considered acceptable for compliance with the requirements of
paragraph (l) of this AD.
(n) Retained Credit for Previous Actions
This paragraph restates the credit given for service information
specified in Note 4 of AD 2000-06-13 R1, Amendment 39-12317 (66 FR
36146, July 11, 2001). This paragraph provides credit for the
modification of the corners of the door frame and the cross beams of
the aft cargo door required by paragraph (l) of this AD, if the
modification was accomplished prior to August 15, 2001 (the
effective date of AD 2000-06-13 R1), using Boeing Service Bulletin
737-52-1079, dated December 16, 1983; Revision 1, dated December 15,
1988; Revision 2, dated July 20, 1989; Revision 3, dated May 17,
1990; or Revision 4, dated February 21, 1991.
(o) New Requirement for Determining Door Configuration
At the applicable time specified in Table 1 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1153, dated
July 13, 2011, except as provided by paragraph (u)(1) of this AD:
Inspect the door to determine the configuration, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-52A1153, dated July 13, 2011.
(p) New Requirements for Certain Doors Subject to Boeing Alert Service
Bulletin 737-52A1079, Revision 7, Dated December 17, 2010
If, during the inspection required by paragraph (o) of this AD,
any door is determined to be from any airplane having line numbers 6
through 873 inclusive, and neither the modification nor the repair
specified in any service bulletin identified in paragraphs (p)(1)
through (p)(7) of this AD has been done as of the effective date of
this AD: Do a one-time HFEC and a one-time ultrasonic inspection for
cracking of the upper and lower corner frames and the upper and
lower cross beams, and do all applicable related investigative and
corrective actions, in accordance with Parts II, III, IV, and VI of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-52A1079, Revision 7, dated December 17, 2010; and, as
applicable, the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-52-1154, dated December 17, 2010, as
revised by Boeing Special Attention Service Bulletin 737-52-1154,
Revision 1, dated August 3, 2011; except as provided by paragraphs
(u)(2) and (u)(3) of this AD. Do the inspections at the applicable
time specified in Table 1 of paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated
December 17, 2010; except as provided by paragraph (u)(4) of this
AD. Do all applicable related investigative and corrective actions
before further flight. If no cracking is found during the initial
inspections, before further flight, do the modification in
accordance with Part III of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated
December 17, 2010. Doing the inspection specified in this paragraph
terminates the inspections required by paragraphs (h) and (k) of
this AD.
(1) Boeing Service Bulletin 737-52-1079, dated December 16,
1983.
(2) Boeing Service Bulletin 737-52-1079, Revision 1, dated
December 15, 1988.
(3) Boeing Service Bulletin 737-52-1079, Revision 2, dated July
20, 1989.
(4) Boeing Service Bulletin 737-52-1079, Revision 3, dated May
17, 1990.
(5) Boeing Service Bulletin 737-52-1079, Revision 4, dated
February 21, 1991.
(6) Boeing Service Bulletin 737-52-1079, Revision 5, dated May
16, 1996.
(7) Boeing Service Bulletin 737-52A1079, Revision 6, dated
November 18, 1999.
(q) Requirements for All Doors Subject to Boeing Alert Service Bulletin
737-52A1079, Revision 7, Dated December 17, 2010
If, during the inspection required by paragraph (o) of this AD,
any door is determined to be from any airplane having line numbers 6
through 873 inclusive: At the applicable time specified in Table 2
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1079, Revision 7, dated December 17, 2010, except as provided
by paragraph (u)(4) of this AD, inspect the lower corner frames to
determine if the door has reinforcement angles, P/N 65C25180-9, -43,
-10, -11, or -12, that were installed as specified in any service
bulletin identified in paragraphs (q)(1) through (q)(5) of this AD.
If any affected reinforcement angle is found, do a one-time general
visual inspection for edge margin and do a detailed inspection for
cracks; in accordance with Part V of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated
December 17, 2010.
(1) Boeing Service Bulletin 737-52-1079, dated December 16,
1983.
(2) Boeing Service Bulletin 737-52-1079, Revision 1, dated
December 15, 1988.
(3) Boeing Service Bulletin 737-52-1079, Revision 2, dated July
20, 1989.
(4) Boeing Service Bulletin 737-52-1079, Revision 3, dated May
17, 1990.
(5) Boeing Service Bulletin 737-52-1079, Revision 4, dated
February 21, 1991.
(r) Corrective Actions for Inspections Specified in Paragraph (q) of
This AD
If, during any inspection required by paragraph (q) of this AD,
any crack is found, or if any edge margin does not meet the
specification identified in Part V of the Accomplishment
Instructions of Boeing Alert
[[Page 71728]]
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010,
before further flight, do the actions specified in paragraphs
(r)(1), (r)(2), and (r)(3) of this AD.
(1) Replace the corner reinforcement angle, in accordance with
Part III of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
(2) Do a one-time detailed inspection or HFEC inspection for
cracking at the forward and aft ends of cross beam D, in accordance
with Part 1 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-52-1154, dated December 17, 2010. If
any cracking is found, before further flight, do all applicable
repairs in accordance with the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737-52-1154, dated December 17,
2010, except as provided by paragraph (u)(2) of this AD.
(3) Do a one-time detailed inspection or ultrasonic inspection
for cracking on the frames, in accordance with Part 2 (detailed
inspection) or Part 8 (ultrasonic inspection) of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 737-52-
1154, dated December 17, 2010, as revised by Boeing Special
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3,
2011. If any cracking is found, before further flight, replace the
frame in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-52A1079, Revision 7, dated December 17,
2010.
(s) Requirements for Doors Subject to Boeing Alert Service Bulletin
737-52A1153, Dated July 13, 2011
If, during the action required by paragraph (o) of this AD, a
door is determined to be from an airplane having line numbers 874
and subsequent: At the applicable time specified in Tables 1 and 2
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1153, dated July 13, 2011, except as provided by paragraph
(u)(1) of this AD, do high frequency and detailed inspections for
cracks in the forward and aft ends of cross beam E, and do all
applicable related investigative and corrective actions, in
accordance with Parts 1, 3, 4, 5, and 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-52A1153, dated
July 13, 2011; and, as applicable, the Accomplishment Instructions
of Boeing Special Attention Service Bulletin 737-52-1154, dated
December 17, 2010, as revised by Boeing Special Attention Service
Bulletin 737-52-1154, Revision 1, dated August 3, 2011; except as
provided by paragraph (u)(2) of this AD. Do all applicable related
investigative and corrective actions at the applicable time
specified in Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 737-52A1153, dated July 13, 2011, except as
provided by paragraph (u)(1) of this AD. If no cracking is found
during the inspections specified in Boeing Alert Service Bulletin
737-52A1153, dated July 13, 2011, at the applicable time specified
in Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-52A1153, dated July 13, 2011, except as
provided by paragraph (u)(1) of this AD, do the modification in
accordance with Parts 5 and 6, as applicable, of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-52A1153, dated
July 13, 2011. Repeat the inspections thereafter at the times
specified in Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011,
until the preventative modification or repair is done to both ends
of cross beam E in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011.
Doing the inspection specified in this paragraph terminates the
inspections required by paragraphs (h) and (k) of this AD.
(t) One Time Inspections for Doors Subject to Boeing Alert Service
Bulletin 737-52A1153, Dated July 13, 2011
If, during the actions required by paragraph (o) of this AD, a
door is determined to be from an airplane having line numbers 874
and subsequent: At the applicable time specified in Tables 3 and 4
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1153, dated July 13, 2011, except as provided by paragraph
(u)(1) of this AD, do a one-time ultrasonic inspection of the frame
and a detailed inspection of the reinforcing angle for cracks of the
forward and aft ends of cross beam E, and do all applicable related
investigative and corrective actions, in accordance with Parts 1, 3,
4, 7, and 8 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-52A1153, dated July 13, 2011; and, as
applicable; the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-52-1154, dated December 17, 2010, as
revised by Boeing Special Attention Service Bulletin 737-52-1154,
Revision 1, dated August 3, 2011; except as provided by paragraph
(u)(2) of this AD. Do all applicable related investigative and
corrective actions before further flight.
(u) Service Information Exceptions
The following exceptions apply to this AD.
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-52A1153, dated July 13, 2011, specifies a
compliance time ``after the original issue date of this service
bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(2) Where Boeing Special Attention Service Bulletin 737-52-1154,
dated December 17, 2010, specifies to contact Boeing for repair,
before further flight, repair using a method approved in accordance
with the procedures specified in paragraph (x) of this AD.
(3) Where Boeing Alert Service Bulletin 737-52A1079, Revision 7,
dated December 17, 2010, specifies to contact Boeing for repair,
before further flight, repair using a method approved in accordance
with the procedures specified in paragraph (x) of this AD.
(4) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010,
specifies a compliance time ``from the date of Revision 7 to this
service bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(v) Supplemental Structural Inspections
The supplemental structural inspections specified in Tables 5
and 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-52A1153, dated July 13, 2011; and Tables 3 and 4 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-52A1079, Revision 7, dated December 17, 2010; are not required
by this AD.
Note 2 to paragraph (v) of this AD: The damage tolerance
inspections specified in Tables 5 and 6 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1153, dated
July 13, 2011; and Tables 3 and 4 of paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated
December 17, 2010; may be used in support of compliance with section
121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations
(14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding
actions specified in the Accomplishment Instructions and figures of
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011; and
Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated
December 17, 2010; are not required by this AD.
(w) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (p), (q), and (r) of this AD, if the actions were
accomplished before the effective date of this AD using any service
information specified in paragraph (w)(1), (w)(2), (w)(3), (w)(4),
(w)(5), (w)(6), or (w)(7) of this AD.
(1) Boeing Service Bulletin 737-52-1079, dated December 16,
1983.
(2) Boeing Service Bulletin 737-52-1079, Revision 1, dated
December 15, 1988.
(3) Boeing Service Bulletin 737-52-1079, Revision 2, dated July
20, 1989.
(4) Boeing Service Bulletin 737-52-1079, Revision 3, dated May
17, 1990.
(5) Boeing Service Bulletin 737-52-1079, Revision 4, dated
February 21, 1991.
(6) Boeing Service Bulletin 737-52-1079, Revision 5, dated May
16, 1996.
(7) Boeing Alert Service Bulletin 737-52A1079, Revision 6, dated
November 18, 1999.
(x) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
ACO, send it to the attention of the person identified in the
Related Information section of this AD. Information may be emailed
to: [email protected].
(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.
[[Page 71729]]
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes ODA that has been authorized by the
Manager, Seattle ACO, to make those findings. For a repair method to
be approved, the repair must meet the certification basis of the
airplane, and the approval must specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 2000-06-13,
Amendment 39-11654 (65 FR 17583, April 4, 2000); and AD 2000-06-13
R1, Amendment 39-12317 (66 FR 36146, July 11, 2001); are approved as
AMOCs for the corresponding requirements of this AD.
(y) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: (425) 917-6450; 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, 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 November 21, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-29170 Filed 12-3-12; 8:45 am]
BILLING CODE 4910-13-P