Airworthiness Directives; The Boeing Company Airplanes, 71723-71729 [2012-29170]
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71723
Proposed Rules
Federal Register
Vol. 77, No. 233
Tuesday, December 4, 2012
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.
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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:
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SUMMARY:
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• Federal eRulemaking Portal: Go to
https://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 https://
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–2012–1156; Directorate Identifier
2011–NM–205–AD’’ at the beginning of
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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 https://
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
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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 https://
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 39-12317 (66 FR 36146, July 11, 2001)
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paragraph
paragraph
paragraph
paragraph
paragraph
(a)
(b)
(c)
(d)
(e)
..................................................................................................................................................................
..................................................................................................................................................................
..................................................................................................................................................................
..................................................................................................................................................................
..................................................................................................................................................................
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
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(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.
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Corresponding requirement
in this proposed AD
paragraph
paragraph
paragraph
paragraph
paragraph
(h)
(i)
(j)
(k)
(l)
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
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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
U.S. Registry
Cost on U.S.
operators
$170 per inspection
cycle.
494
$0
$340 per inspection
cycle.
494
$83,890 per
inspection
cycle.
$167,960 per
inspection
cycle.
144 work-hours × $85
per hour = $12,240.
$5,430
$17,670 .......................
494
$8,728,980
1 work-hour × $85 per
hour = $85.
6 work-hours × $85 per
hour = $510 per inspection cycle.
59 work-hours × $85
per hour = $5,015.
$0
$85 ..............................
581
$49,385
$0
$510 per inspection
cycle.
581
$30,536
$35,551 .......................
(1)
$296,310 per
inspection
cycle.
Unknown.
Action
Labor cost
Detailed inspection [retained action from existing AD 2000–06–13 R1, Amendment
39-12317 (66 FR 36146, July 11, 2001)].
High frequency eddy current inspection [retained action from existing AD 2000–06–13
R1, Amendment 39-12317 (66 FR 36146,
July 11, 2001)].
Modification [retained action from existing AD
2000–06–13 R1, Amendment 39-12317 (66
FR 36146, July 11, 2001)].
Determination of door configuration [new proposed action].
Inspections [new proposed action] ....................
2 work-hours × $85 per
hour = $170 per inspection cycle.
4 work-hours × $85 per
hour = $340 per inspection cycle.
$0
Modification [new proposed action] ...................
Parts cost
Cost per product
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
Parts cost
Action
Labor cost
Related investigative and corrective actions ........................................................
59 work-hours × $85 per hour =
$5,015.
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Authority for This Rulemaking
Regulatory Findings
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.
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
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Cost per
product
$30,536
$35,551
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2000–06–13 R1, Amendment 39–12317
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Federal Register / Vol. 77, No. 233 / Tuesday, December 4, 2012 / Proposed Rules
(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.
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(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.
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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
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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.
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(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,
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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
PO 00000
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Sfmt 4702
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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
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srobinson on DSK4SPTVN1PROD with
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
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16:10 Dec 03, 2012
Jkt 229001
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
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
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: 9-ANMSeattle-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.
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Federal Register / Vol. 77, No. 233 / Tuesday, December 4, 2012 / Proposed Rules
(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.
[Docket No. FAA–2012–1222; Directorate
Identifier 2012–NM–134–AD]
control unit (PCU), and replacing any
PCU on which the bearing exceeds
allowable limits with a serviceable PCU.
Since we issued that AD, we have
determined that additional airplanes are
affected by the identified unsafe
condition. This proposed AD would add
airplanes to the applicability in the
existing AD. We are proposing this AD
to detect and correct excessive freeplay
of the swaged bearings, which could
lead to excessive airframe vibrations
and difficulties in pitch control, and
consequent loss of controllability of the
airplane.
DATES: We must receive comments on
this proposed AD by January 18, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Bombardier,
Inc., Q-Series Technical Help Desk, 123
Garratt Boulevard, Toronto, Ontario
M3K 1Y5, Canada; telephone 416–375–
4000; fax 416–375–4539; email
thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com.
You may review copies of the
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA.
For information on the availability of
this material at the FAA, call 425–227–
1221.
RIN 2120–AA64
Examining the AD Docket
(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: 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
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain Bombardier, Inc.
Model DHC–8–400 series airplanes. The
existing AD currently requires a freeplay check for excessive free-play of the
shaft swaged bearing installed in the
tailstock end of each elevator power
srobinson on DSK4SPTVN1PROD with
SUMMARY:
VerDate Mar<15>2010
16:10 Dec 03, 2012
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You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Cesar Gomez, Aerospace Engineer,
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
71729
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office (ACO), 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7318; fax (516) 794–5531.
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–2012–1222; Directorate Identifier
2012–NM–134–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
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 June 14, 2011, we issued AD
2011–13–08, Amendment 39–16731 (76
FR 37253, June 27, 2011). That AD
required actions intended to address an
unsafe condition on Bombardier, Inc.
Model DHC–8–400 series airplanes.
Since we issued the existing AD (76
FR 37253, June 27, 2011), we have
determined that additional airplanes are
affected by the identified unsafe
condition. Transport Canada Civil
Aviation (TCCA), which is the aviation
authority for Canada, has issued
Canadian Airworthiness Directive CF–
2010–28R1, dated June 12, 2012
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Several reports have been received on the
elevator power control units (PCUs) where
the shaft (tailstock) swaged bearing liners had
shown a higher than normal rate of wear.
Investigation revealed that the excessive wear
was due to the paint contamination between
the bearing roller and bearing liner. The
bearing paint contamination is known to be
abrasive and could seize the bearing.
This condition, if not corrected, could lead
to excessive airframe vibrations and
difficulties in aircraft pitch control.
This [TCCA] directive mandates a free-play
check of the shaft swaged bearing installed in
the elevator PCU tailstock end and
replacement of the shaft swaged bearings if
excessive free-play is found.
E:\FR\FM\04DEP1.SGM
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]]>Agencies
[Federal Register Volume 77, Number 233 (Tuesday, December 4, 2012)]
[Proposed Rules]
[Pages 71723-71729]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-29170]
========================================================================
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.
========================================================================
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 https://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 https://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-2012-1156;
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 https://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 https://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: 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.
[[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:
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 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
