[Federal Register Volume 77, Number 120 (Thursday, June 21, 2012)]
[Proposed Rules]
[Pages 37332-37337]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-15181]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 77, No. 120 / Thursday, June 21, 2012 /
Proposed Rules
[[Page 37332]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0724; Directorate Identifier 2010-NM-181-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
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SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for certain The Boeing Company Model 757-200, -200PF, and -200CB
series airplanes powered by Rolls-Royce engines. That NPRM proposed to
supersede an existing AD that requires repetitive inspections of the
shim installation between the drag brace fitting vertical flange and
bulkhead, and repair if necessary; for certain airplanes, an inspection
for cracking of the four critical fastener holes in the horizontal
flange, and repair if necessary; and, for airplanes without conclusive
records of previous inspections, performing the existing actions. That
NPRM proposed to reduce the repetitive inspection interval, add
repetitive detailed inspections for cracking of the bulkhead, and
repair if necessary; extend the repetitive intervals for certain
airplanes by also doing repetitive ultrasonic inspections for cracking
of the bulkhead, and repair if necessary; and an option for the high
frequency eddy current inspection for cracking of the critical fastener
holes, and repair if necessary. That NPRM was prompted by reports of
loose fasteners and cracks at the joint common to the aft torque
bulkhead and strut-to-diagonal brace fitting, and one report of such
damage occurring less than 3,000 flight cycles after the last
inspection. This action revises that NPRM by adding a terminating
action for certain repetitive inspections. We are proposing the
supplemental NPRM to detect and correct cracks, loose and broken bolts,
and shim migration in the joint between the aft torque bulkhead and the
strut-to-diagonal brace fitting, which could result in damage to the
strut and consequent separation of the strut and engine from the
airplane. Since these actions impose an additional burden over that
proposed in the NPRM, we are reopening the comment period to allow the
public the chance to comment on these proposed changes.
DATES: We must receive comments on the supplemental NPRM by August 6,
2012.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, 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, WA 98124-2207; phone: 206-544-5000,
extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO),
FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-
917-6440; fax: 425-917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0724;
Directorate Identifier 2010-NM-181-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We issued an NPRM to amend 14 CFR part 39 to supersede AD 2008-05-
10, Amendment 39-15404 (73 FR 11347, March 3, 2008), to include an AD
applies to certain The Boeing Company Model 757-200, -200PF, and -200CB
series airplanes powered by Rolls-Royce engines. That NPRM was
published in the Federal Register on August 24, 2011 (76 FR 52901).
That NPRM proposed to continue to repetitive inspections of the shim
installation between the drag brace fitting vertical flange and
bulkhead, and repair if necessary; for certain airplanes, an inspection
for cracking of the four critical fastener holes in the horizontal
flange, and repair if necessary; and, for airplanes without conclusive
records of previous inspections, performing the existing actions.
Additionally, the existing AD requires that the existing
[[Page 37333]]
action be performed on airplanes without conclusive records of previous
inspections. That NPRM proposed to reduce the repetitive inspection
interval, and add repetitive detailed inspections for cracking of the
bulkhead, and repair if necessary. That NPRM proposed an option, for
certain airplanes, to extend the repetitive intervals by also doing
repetitive ultrasonic inspections for cracking of the bulkhead, and
repair if necessary; and proposed an option to the high frequency eddy
current inspection for cracking of the critical fastener holes, and
repair if necessary.
Actions Since Previous NPRM (76 FR 52901, August 24, 2011) Was Issued
Since we issued the previous NPRM (76 FR 52901, August 24, 2011),
new service information has been issued that specifies additional
actions that are necessary to address the identified unsafe condition,
and also describes a terminating action for the repetitive inspections
on certain airplanes.
Comments
We gave the public the opportunity to comment on the previous NPRM
(76 FR 52901, August 24, 2011). The following presents the comments
received on the NPRM and the FAA's response to each comment.
Agreement With the Previous NPRM (76 FR 52901, August 24, 2011)
Continental Airlines (Continental) stated it concurs in general
with previous NPRM (76 FR 52901, August 24, 2011) to mandate Boeing
Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010,
inspections.
Request To Reference Revised Service Information
Continental, UPS, European Air Transport Leipzig GmbH (EATL), and
FedEx requested that the previous NPRM (76 FR 52901, August 24, 2011)
be changed to include Boeing Alert Service Bulletin 757-54A0047,
Revision 5, dated June 9, 2011. The commenters stated this revised
service information includes a terminating action for the repetitive
inspections.
We agree because Boeing Alert Service Bulletin 757-54A0047,
Revision 5, dated June 9, 2011, includes terminating action to address
the unsafe condition. Boeing Alert Service Bulletin 757-54A0047,
Revision 5, dated June 9, 2011, describes procedures for certain
airplanes for replacing the horizontal and vertical flange fasteners in
the strut-to-diagonal brace fitting on the number 1 and number 2 struts
with new fasteners, and doing related investigative and corrective
actions if necessary. The related investigative action is an eddy
current inspection for cracking of the critical fastener holes in the
horizontal and vertical flange. The corrective action is contacting
Boeing for repair instructions and doing the repair. We have changed
this supplemental NPRM to refer to Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011, and have made the terminating
action specified in this service information mandatory. We have also
added paragraph (p) in this supplemental NPRM to provide credit for
actions accomplished before the effective date of the AD using Boeing
Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010.
Request To Include Alternative Method of Compliance (AMOC) in Previous
NPRM (76 FR 52901, August 24, 2011)
Continental requested a paragraph be added to the previous NPRM (76
FR 52901, August 24, 2011) that approves accomplishment of the
terminating modification specified in Boeing Alert Service Bulletin
757-54A0047, Revision 5, dated June 9, 2011, as an AMOC with the
actions specified in paragraphs (g), (h), (l), (q), and (r) of the
previous NPRM. The commenter did not provide any justification for this
request.
We disagree with adding an AMOC provision to the supplemental NPRM.
As previously stated, we are changing the supplemental NPRM to mandate
the terminating action specified in Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011, which would terminate the
inspections specified in paragraphs (g), (h), (j), and (m) of the
supplemental NPRM for Group 1, Configuration 2 airplanes; and Group 2
airplanes; as identified in Boeing Alert Service Bulletin 757-54A0047,
Revision 5, dated June 9, 2011. These supplemental NPRM paragraphs are
the same paragraphs specified by the commenter (paragraphs (j) and (m)
of the supplemental NPRM correspond to paragraphs (l) and (q) in the
previous NPRM (76 FR 52901, August 24, 2011)). The commenter also
included paragraph (r) of the previous NPRM (which is paragraph (n) in
the supplemental NPRM); however, that paragraph is not pertinent since
it provides the compliance times for paragraph (m) in the supplemental
NPRM. Termination of the inspections specified in paragraphs (g), (h),
(j), and (m) of this supplemental NPRM, through accomplishment of the
modification required by paragraph (o) of this supplemental NPRM, has
the same result as the AMOC requested by the commenter, since use of
Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9,
2011, is being proposed. We have not changed the supplemental NPRM in
this regard.
Request To Add Actions Specified in Revised Service Information
Boeing proposed language for three new paragraphs to the previous
NPRM (76 FR 52901, August 24, 2011), which correspond to paragraphs
(s), (t), and (u) of the previous NPRM, that would require certain
actions specified in Boeing Alert Service Bulletin 757-54A0047,
Revision 5, dated June 9, 2011. The actions in Boeing's proposed
paragraphs included installation of larger diameter fasteners, as
specified in Boeing Alert Service Bulletin 757-54A0047, Revision 5,
dated June 9, 2011, ``within 9,000 flight cycles or 54 months,
whichever is earlier, after the effective date of the AD;'' crack
repair instructions for cracking found during the fastener
modification; and termination of inspections required in paragraphs
(h), (l)(2), and (q) of the previous NPRM.
We partially agree. We agree to refer to Boeing Alert Service
Bulletin 757-54A0047, Revision 5, dated June 9, 2011, because it
provides additional actions and a modification to address the unsafe
condition for certain airplanes. We disagree with adding the specific
paragraphs proposed by Boeing because we are issuing a supplemental
NPRM that proposes to mandate Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011. Therefore, the paragraphs
proposed by Boeing that specify installing larger diameter fasteners
and the compliance time are unnecessary. We have not changed the
supplemental NPRM in this regard.
Boeing also proposed a paragraph that defines the terminating
action for the repetitive inspections required by paragraphs (h),
(l)(2), and (q) of the previous NPRM (76 FR 52901, August 24, 2011).
Part of the commenter's proposed terminating action paragraph for Group
1, Configuration 1 airplanes; and Group 2 airplanes; is unnecessary.
Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9,
2011, specified in the supplemental NPRM, already includes this
information. Additionally, the commenter's proposed terminating action
paragraph stated that modification of the strut, in accordance with
Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9,
2011, terminates the repetitive inspections of paragraphs (h), (l)(2),
and (q) of the previous NPRM for Group 1, Configuration 1 airplanes.
[[Page 37334]]
We disagree with changing the supplemental NPRM to include this
information as it is redundant to the information included in Boeing
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011.
This service information defines Group 1, Configuration 1 airplanes, as
airplanes that have not accomplished the modifiction described in
Boeing Service Bulletin 757-54-0035, thus the signficance of the strut
modification accomplishment is clearly specified. We have not changed
the supplemental NPRM in this regard.
Request To Add an AMOC Into the Previous NPRM (76 FR 52901, August 24,
2011)
Boeing requested we add a paragraph to the previous NPRM (76 FR
52901, August 24, 2011) stating that inspections and repairs done in
accordance with Boeing Alert Service Bulletin 757-54A0047, Revision 5,
dated June 9, 2011, are an AMOC for the corresponding requirements of
the AD. Boeing stated that the inspections and repairs for Boeing Alert
Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011, are
equivalent to the corresponding inspections and repairs specified in
Boeing Alert Service Bulletin 757-54A0047, Revision 4, dated June 24,
2010, and since Boeing Alert Service Bulletin 757-54A0047, Revision 5,
dated June 9, 2011, is already published and in use by the operators,
this would eliminate the need for a separate global AMOC for Boeing
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011,
relative to this AD.
We partially agree. The previous NPRM (76 FR 52901, August 24,
2011) did reference Boeing Alert Service Bulletin 757-54A0047, Revision
4, dated June 24, 2010. We agree that the actions specified in Boeing
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011, are
equivalent to the corresponding actions specified in Boeing Alert
Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010. However,
as stated previously, the supplemental NPRM references Boeing Alert
Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011,
eliminating the need for an AMOC. We have not changed the supplemental
NPRM in this regard.
Explanation of Additional Changes Made to This Supplemental NPRM
We have revised certain headings throughout this supplemental NPRM.
The credit for previous accomplishment of the actions required by
AD 2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008),
specified in paragraphs (n) and (o) of the previous NPRM (76 FR 52901,
August 24, 2011), has been moved to paragraph (p) of the supplemental
NPRM.
We have revised the heading and wording for paragraphs (n) and (o)
of this AD. This change does not affect the intent of those paragraphs.
We revised paragraph (l) of this supplemental NPRM to refer to
paragraphs (b) and (d) of AD 2004-12-07, Amendment 39-13666 (69 FR
33561, June 16, 2004), instead of paragraphs (b) and (c) of AD 2004-12-
07, because paragraph (d) of AD 2004-12-07 contains the inspection of
the fastener holes and inspection of the fasteners common to the lower
spar fitting and strut aft bulkhead. Paragraph (c) of AD 2004-12-07 is
a preliminary inspection of the middle gusset of the inboard side load
fitting. We also revised paragraph (p) of this supplemental NPRM to
reference paragraph (d) of AD 2004-12-07, instead of paragraph (c) of
AD 2004-12-07.
FAA's Determination
We are proposing this supplemental NPRM 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. Certain changes described above expand the scope of the
original NPRM (76 FR 52901, August 24, 2011). As a result, we have
determined that it is necessary to reopen the comment period to provide
additional opportunity for the public to comment on this supplemental
NPRM.
Proposed Requirements of the Supplemental NPRM
This supplemental NPRM would retain all the requirements of AD
2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008); reduce the
repetitive inspection interval for cracking, and add repetitive
detailed inspections for cracking of the bulkhead, and repair if
necessary. This supplemental NPRM would also, for certain airplanes,
add an option to extend the repetitive intervals by also doing
repetitive ultrasonic inspections for cracking of the bulkhead, and
repair if necessary; and add an option to the high frequency eddy
current inspection for cracking of the critical fastener holes, and
repair if necessary. This supplemental NPRM would also require
replacing certain horizontal and vertical flange fasteners in the
strut-to-diagonal brace fittings and accomplishing the actions
specified in the service information described previously, except as
discussed under ``Differences Between the Supplemental NPRM and the
Service Information.''
Differences Between the Supplemental NPRM and the Service Information
Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June
9, 2011, specifies to contact the manufacturer for instructions on how
to repair certain conditions, but this supplemental NPRM 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.
Accomplishment of the actions required in paragraph (o) of this
supplemental NPRM would terminate the inspection requirements of
paragraphs (g), (h), (j), and (m) of this supplemental NPRM for Group
1, Configuration 2 airplanes; and Group 2 airplanes; as identified in
Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9,
2011.
Costs of Compliance
We estimate that this proposed AD affects 309 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Part I Inspection on fasteners 28 work-hours x $85 $0 $2,380 per $735,420 per
and shims--vertical flange per hour = $2,380 inspection cycle inspection cycle
[retained actions from AD 2008- per inspection
05-10, Amendment 39-15404 (73 FR cycle
11347, March 3, 2008)]
[[Page 37335]]
Part II Inspection on fasteners-- 6 work-hours x $85 0 $510 per inspection $157,590 per
horizontal flange [retained per hour = $510 per cycle inspection cycle.
actions from AD 2008-05-10, inspection cycle
Amendment 39-15404 (73 FR 11347,
March 3, 2008)]
Part IV inspection on critical 6 work-hours x $85 0 $510 per inspection $157,590 per
fasteners--horizontal flange per hour = $510 per cycle inspection cycle.
[retained actions from AD 2008- inspection cycle
05-10, Amendment 39-15404 (73 FR
11347, March 3, 2008)]
Part II Additional inspection 10 work-hours x $85 0 $850 per inspection $262,650 per
actions on fasteners--horizontal per hour = $850 per cycle inspection cycle.
flange [new proposed action] inspection cycle
Part IV inspection on critical 8 to 22 work-hours x 0 $680 to $1,870 per $210,120 to $577,830
fasteners--horizontal flange $85 per hour = $680 inspection cycle per inspection
[new proposed action] to $1,870 per cycle.
inspection cycle
Part V fastener replacement Up to 37 work-hours 750 Up to $3,895 per Up to $1,203,555 per
flange [new proposed action] x $85 per hour = strut strut.
$3,145 per strut
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation Programs''
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We 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 this 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) 2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2011-0724; Directorate Identifier
2010-NM-181-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by August 6,
2012.
(b) Affected ADs
This AD supersedes AD 2008-05-10, Amendment 39-15404 (73 FR
11347, March 3, 2008).
(c) Applicability
This AD applies to The Boeing Company Model 757-200, -200PF, and
-200CB series airplanes; certificated in any category; line numbers
1 through 1048 inclusive; powered by Rolls-Royce engines.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 54, Nacelles/Pylons.
(e) Unsafe Condition
This AD was prompted by reports of loose fasteners and cracks at
the joint common to the aft torque bulkhead and strut-to-diagonal
brace fitting, and one report of such damage occurring less than
3,000 flight cycles after the last inspection. We are issuing this
AD to detect and correct cracks, loose and broken bolts, and shim
migration in the joint between the aft torque bulkhead and the
strut-to-diagonal brace fitting, which could result in damage to the
strut and consequent separation of the strut and engine from the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained One-Time Inspection and Repair With Optional Inspection
Method, With Reduced Repetitive Intervals and New Optional Inspection
Method
This paragraph restates the one-time inspection and repair with
optional inspection method required by paragraph (g) of AD 2008-05-
10, Amendment 39-15404 (73 FR 11347, March 3, 2008), with reduced
repetitive intervals, and a new optional inspection method, with
revised service information. For airplanes identified in paragraphs
(g)(1) and (g)(2) of this AD: Within 90 days after August 24, 2007
(the effective date of AD 2007-16-13, Amendment 39-15152 (72 FR
44753, August 9, 2007)), do a high frequency eddy current (HFEC)
inspection for cracking of the four critical fastener holes in the
horizontal flange and, before further flight, do all applicable
[[Page 37336]]
repairs, in accordance with Part IV of the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-54A0047, Revision
3, dated June 27, 2007; Boeing Alert Service Bulletin 757-54A0047,
Revision 4, dated June 24, 2010; or Boeing Alert Service Bulletin
757-54A0047, Revision 5, dated June 9, 2011; except as required by
paragraph (i)(3) of this AD. As of the effective date of this AD,
only Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated
June 9, 2011, may be used to accomplish the actions required by this
paragraph. Doing an ultrasonic inspection for cracking of the
fasteners, in accordance with Part IV of the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-54A0047, Revision
4, dated June 24, 2010; or Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011; is an acceptable method for
compliance with the HFEC inspection requirement of this paragraph.
(1) Airplanes on which findings on the horizontal or vertical
fasteners or the shims led to a rejection of any fastener during the
actions specified in Boeing Alert Service Bulletin 757-54A0047,
dated November 13, 2003; or Boeing Service Bulletin 757-54A0047,
Revision 1, dated March 24, 2005.
(2) Airplanes that had equivalent findings prior to Boeing Alert
Service Bulletin 757-54A0047, dated November 13, 2003, except for
findings on airplanes identified as Group 1, Configuration 2, in
Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated June
27, 2007, that were prior to the incorporation of Boeing Service
Bulletin 757-54-0035.
(h) Retained Repetitive Inspection and Repair, With Reduced Interval
This paragraph restates the repetitive inspection and repair
required by paragraph (h) of AD 2008-05-10, Amendment 39-15404 (73
FR 11347, March 3, 2008), with reduced repetitive intervals and
revised service information. At the applicable initial times
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 757-54A0047, Revision 3, dated June 27, 2007, except as
required by paragraphs (i)(1) and (i)(2) of this AD: Do the
inspections specified in paragraphs (h)(1), (h)(2), and (h)(3) of
this AD, and before further flight, do all the applicable related
investigative actions and repairs, by doing all the actions
specified in Parts I and II of the Accomplishment Instructions of
Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated June
27, 2007; or by doing all the actions in Part I and in Step 2 of
Part II of the Accomplishment Instructions of Boeing Alert Service
Bulletin 757-54A0047 Revision 4, dated June 24, 2010, or Boeing
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011,
except as required by paragraph (i)(3) of this AD. As of the
effective date of this AD, only Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011, may be used to accomplish
the actions required by this paragraph. Repeat the inspections
required by this paragraph at the times specified in paragraph
(h)(4) of this AD.
(1) Do detailed inspections of the shim installations between
the vertical flange and bulkhead to determine if there are signs of
movement.
(2) Do detailed inspections of the four fasteners in the
vertical flange to determine if there are signs of movement or if
there are gaps under the head or collar.
(3) Do detailed inspections of the fasteners that hold the strut
to the horizontal flange of the strut-to-diagonal brace fitting to
determine if there are signs of movement or if there are gaps under
the head or collar.
(4) Repeat the inspections required by paragraph (h) of this AD
at the earlier of the times specified in paragraphs (h)(4)(i) and
(h)(4)(ii) of this AD. Thereafter, repeat the inspections at
intervals not to exceed the applicable intervals specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
757-54A0047, Revision 5, dated June 9, 2011.
(i) At intervals not to exceed the applicable intervals
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 757-54A0047, Revision 3, dated June 27, 2007.
(ii) At intervals not to exceed the applicable intervals
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 757-54A0047, Revision 5, dated June 9, 2011; or within 90
days after the effective date of this AD; whichever occurs later.
(i) Retained Exceptions to Alert Service Bulletin Procedures
This paragraph restates the exceptions to alert service bulletin
procedures required by paragraphs (i), (j), and (k) of AD 2008-05-
10, Amendment 39-15404 (73 FR 11347, March 3, 2008), with revised
service information.
(1) Where Boeing Alert Service Bulletin 757-54A0047, Revision 3,
dated June 27, 2007, specifies a compliance time relative to ``the
date on this service bulletin,'' this AD requires compliance within
the corresponding specified time relative to the effective date of
AD 2007-16-13, Amendment 39-15152 (72 FR 44753, August 9, 2007).
(2) Where Boeing Alert Service Bulletin 757-54A0047, Revision 3,
dated June 27, 2007, specifies a compliance time relative to the
``date of issuance of airworthiness certificate,'' this AD requires
compliance within the corresponding time relative to the date of
issuance of the original standard airworthiness certificate or the
date of issuance of the original export certificate of
airworthiness.
(3) If any crack is found during any inspection required by this
AD, and Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated
June 27, 2007; Boeing Alert Service Bulletin 757-54A0047, Revision
4, dated June 24, 2010; or Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011; specifies to contact Boeing
for appropriate action: Before further flight, repair the crack
using a method approved in accordance with the procedures specified
in paragraph (q) of this AD.
(j) Retained Inspection/Repair for Airplanes for Which There Are No
Conclusive Inspection Records
This paragraph restates the inspection/repair requirements for
airplanes for which there are no conclusive inspection records, as
required by paragraph (l) of AD 2008-05-10, Amendment 39-15404 (73
FR 11347, March 3, 2008), with revised service information. For
airplanes for which there are no conclusive records showing no loose
or missing fasteners during previous inspections done in accordance
with the requirements of AD 2007-16-13, Amendment 39-15152 (72 FR
44753, August 9, 2007); or AD 2005-12-04, Amendment 39-14120 (70 FR
34313 June 14, 2005): Do the actions specified in paragraphs (j)(1)
and (j)(2) of this AD, at the times specified in those paragraphs,
as applicable.
(1) Within 90 days after March 18, 2008 (the effective date of
AD 2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008)), do
the actions specified in paragraph (g) of this AD, except as
required by paragraph (i)(3) of this AD.
(2) At the applicable initial times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 757-54A0047,
Revision 3, dated June 27, 2007, do the actions specified in
paragraph (h) of this AD, except as required by paragraphs (i)(2)
and (k) of this AD. And, before further flight, do all applicable
related investigative actions and repairs, by doing all the actions
specified in Parts I and II of the Accomplishment Instructions of
Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated June
27, 2007; or in Part 1 and in Step 2 of Part II of the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
54A0047 Revision 4, dated June 24, 2010, or Boeing Alert Service
Bulletin 757-54A0047, Revision 5, dated June 9, 2011, except as
required by paragraph (i)(3) of this AD. As of the effective date of
this AD, only Boeing Alert Service Bulletin 757-54A0047, Revision 5,
dated June 9, 2011, may be used to accomplish the actions required
by this paragraph. Repeat the actions specified in paragraph (h) of
this AD at the times specified in paragraph (h)(4) of this AD.
(k) Retained Exception to Alert Service Bulletin Procedures
This paragraph restates the exception to alert service bulletin
procedures required by paragraph (m) of AD 2008-05-10, Amendment 39-
15404 (73 FR 11347, March 3, 2008). Where Boeing Alert Service
Bulletin 757-54A0047, Revision 3, dated June 27, 2007, specifies a
compliance time relative to ``the date on this service bulletin,''
this AD requires compliance within the corresponding specified time
relative to the effective date of AD 2008-05-10.
(l) Retained Acceptable Method of Compliance With Certain Requirements
of AD 2004-12-07, Amendment 39-13666 (69 FR 33561 June 16, 2004)
This paragraph restates an acceptable method of compliance with
certain requirements of AD 2004-12-07, Amendment 39-13666 (69 FR
33561 June 16, 2004), specified by paragraph (p) of AD 2008-05-10,
Amendment 39-15404 (73 FR 11347, March 3, 2008). Accomplishing the
actions specified in paragraphs (g) and (h) of this AD terminates
the requirements specified in paragraphs (b) and (d) of AD 2004-12-
07.
[[Page 37337]]
(m) New Repetitive Inspections and Repair
At the applicable initial compliance times specified in
paragraph (n) of this AD: Do the applicable actions specified in
paragraph (m)(1) or (m)(2) of this AD, in accordance with Step 3 of
Part II of the Accomplishment Instructions of Boeing Alert Service
Bulletin 757-54A0047, Revision 4, dated June 24, 2010; or Boeing
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011.
If no cracking is found, repeat the inspections thereafter at
intervals not to exceed the applicable intervals specified in
paragraph 1.E., ``Compliance,'' of the Accomplishment Instructions
of Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June
9, 2011. If any crack is found during any inspection required by
this paragraph, before further flight, repair the crack using a
method approved in accordance with the procedures specified in
paragraph (q) of this AD.
(1) For Group 1, Configuration 1 airplanes identified in Boeing
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011:
Do the actions specified in paragraph (m)(1)(i) or (m)(1)(ii) of
this AD.
(i) Do a detailed inspection for cracking of the bulkhead in the
area around the access door cutout and around the critical fasteners
in the horizontal flange.
(ii) Do a detailed inspection for cracking of the bulkhead in
the area around the access door cutout and around the critical
fasteners in the horizontal flange, and do an ultrasonic inspection
for cracking of the bulkhead around the fasteners in the horizontal
flange. Doing the actions in this paragraph extends the repetitive
intervals of the inspections required by paragraph (n) of this AD.
(2) For Group 1, Configuration 2 airplanes; and Group 2
airplanes; identified in Boeing Alert Service Bulletin 757-54A0047,
Revision 5, dated June 9, 2011: Do a detailed inspection for
cracking of the bulkhead in the area around the access door cutout
and around the critical fasteners in the horizontal flange.
(n) New Compliance Times for Paragraph (m) of This AD
At the applicable times specified in paragraphs (n)(1) and
(n)(2) of this AD, do the actions required by paragraph (m) of this
AD.
(1) For Group 1, Configuration 1 airplanes identified in Boeing
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011:
At the later of the times specified in paragraph (n)(1)(i) or
(n)(1)(ii) of this AD.
(i) Within 1,800 flight cycles after accomplishing the most
recent inspection required by paragraph (h) or (j) of this AD.
(ii) Within 90 days after the effective date of this AD.
(2) For Group 1, Configuration 2 airplanes; and Group 2
airplanes; identified in Boeing Alert Service Bulletin 757-54A0047,
Revision 5, dated June 9, 2011: At the later of the times specified
in paragraph (n)(2)(i) or (n)(2)(ii) of this AD.
(i) Within 3,000 flight cycles after accomplishing the most
recent inspection required by paragraph (h) or (j) of this AD.
(ii) Within 90 days after the effective date of this AD.
(o) New Terminating Action for Certain Airplanes: Fastener Replacement
For Group 1, Configuration 2 airplanes; and Group 2 airplanes;
as identified in Boeing Alert Service Bulletin 757-54A0047, Revision
5, dated June 9, 2011: Within 9,000 flight cycles or 54 months after
the effective date of this AD, whichever occurs first, replace the
horizontal and vertical flange fasteners in the strut-to-diagonal
brace fitting on the number 1 and number 2 struts with new fasteners
and do all related investigative and applicable corrective actions,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011, except
where Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated
June 9, 2011, specifies to contact Boeing for repair instructions,
before further flight, repair using a method approved in accordance
with the procedures specified in paragraph (q) of this AD. Do all
related investigative and corrective actions before further flight.
Accomplishment of the actions required in paragraph (o) of this AD
terminates the inspection requirements of paragraphs (g), (h), (j),
and (m) of this AD for Group 1, Configuration 2 airplanes; and Group
2 airplanes; as identified in Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011.
(p) Credit for Previous Actions
(1) Except for the actions specified in paragraphs (j), (m), and
(o) of this AD, this paragraph provides credit for the actions
required by paragraphs (g) and (h) of this AD, if those actions were
done before March 18, 2008 (the effective date of AD 2008-05-10,
Amendment 39-15404 (73 FR 11347, March 3, 2008), using Boeing
Service Bulletin 757-54A0047, Revision 1, dated March 24, 2005; or
Boeing Alert Service Bulletin 757-54A0047, Revision 2, dated January
31, 2007.
(2) This paragraph provides credit for the initial inspection
required by paragraph (h) of this AD, if that inspection was done
before June 29, 2005 (the effective date of AD 2005-12-04, Amendment
39-14120 (70 FR 34313, June 14, 2005)), using the actions required
by paragraph (b) or (d), as applicable, of AD 2004-12-07, Amendment
39-13666 (69 FR 33561, June 16, 2004).
(q) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane and the approval must
specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 2004-12-07,
Amendment 39-13666 (69 FR 33561, June 16, 2004), are approved as
AMOCs for the corresponding provisions of this AD.
(5) AMOCs approved previously in accordance with AD 2005-12-04,
Amendment 39-14120 (70 FR 34313, June 14, 2005), are approved as
AMOCs for the corresponding provisions of this AD.
(6) AMOCs approved previously in accordance with AD 2007-16-13,
Amendment 39-15152 (72 FR 44753, August 9, 2007), are approved as
AMOCs for the corresponding provisions of this AD.
(7) AMOCs approved previously in accordance with AD 2008-05-10,
Amendment 39-15404 (73 FR 11347, March 3, 2008), are approved as
AMOCs for the corresponding provisions of this AD.
(r) Related Information
(1) For more information about this AD, contact Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft
Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; phone 425-917-6440; fax 425-917-6590; email:
[email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; phone: 206-
544-5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on June 14, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-15181 Filed 6-20-12; 8:45 am]
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