Airworthiness Directives; The Boeing Company Model 757-200, -200PF, and -200CB Series Airplanes, 52901-52905 [2011-21668]
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Federal Register / Vol. 76, No. 164 / Wednesday, August 24, 2011 / Proposed Rules
(j) 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; e-mail
me.boecom@boeing.com; Internet https://
www.myboeingfleet.com. You may review
copies of the referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on August
12, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–21667 Filed 8–23–11; 8:45 am]
BILLING CODE 4910–13–P
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 Model 757–200, –200PF, and
–200CB Series 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 the products listed above.
The existing AD currently requires
repetitive inspections of the shim
installation between the engine strut
vertical flange and bulkhead, and repair
if necessary. The existing AD also
requires, for certain airplanes, an
inspection for cracking of the four
critical fastener holes in the horizontal
flange, and repair if necessary.
Additionally, the existing AD requires
that the existing action be performed on
airplanes without conclusive records of
previous inspections. Since we issued
that AD, we have received 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 proposed AD would
reduce the repetitive inspection
interval, and add repetitive detailed
inspections for cracking of the
bulkhead, and repair if necessary. This
proposed AD would also provide an
option, for certain airplanes, to extend
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SUMMARY:
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the repetitive intervals by also doing
repetitive ultrasonic inspections for
cracking of the bulkhead, and repair if
necessary. This proposed AD would
also add an option for the high
frequency eddy current inspection for
cracking of the critical fastener holes,
and repair if necessary. We are
proposing 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-todiagonal brace fitting, which could
result in damage to the strut and
consequent separation of the strut and
engine from the airplane.
DATES: We must receive comments on
this proposed AD by October 11, 2011.
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: Deliver to Mail
address above between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207;
phone: 206–544–5000, extension 1; fax:
206–766–5680; e-mail:
me.boecom@boeing.com; Internet:
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at 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:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, Seattle
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52901
Aircraft Certification Office (ACO),
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; phone: 425–
917–6440; fax: 425–917–6590; e-mail:
Nancy.Marsh@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–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 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 February 22, 2008, we issued AD
2008–05–10, Amendment 39–15404 (73
FR 11347, March 3, 2008), for certain
Boeing Model 757–200, –200PF, and
–200CB series airplanes powered by
Rolls-Royce engines. That AD requires
repetitive inspections of the shim
installation between the engine strut
vertical flange and bulkhead, and repair
if necessary. That AD also requires, for
certain airplanes, an inspection for
cracking of the four critical fastener
holes in the horizontal flange, and
repair if necessary. That AD resulted
from reports of cracking in the pylon
under bolts that appear to be
undamaged during the existing AD
inspections. That AD also resulted from
our determination that operators did not
maintain records of previous
inspections that are necessary to
determine the appropriate corrective
actions. We issued that AD to detect and
correct cracks, loose and broken bolts,
and shim migration in the joint between
the aft torque bulkhead and the strut-todiagonal brace fitting, which could
result in damage to the strut and
consequent separation of the strut and
engine from the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2008–05–10, we
have received reports of loose fasteners
and cracks at the joint common to the
aft torque bulkhead and strut-todiagonal brace fitting and one report of
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such damage found fewer than 3,000
flight cycles after the last inspection.
Related Service Information
We reviewed Boeing Alert Service
Bulletin 757–54A0047, Revision 4,
dated June 24, 2010. This service
information reduces the repetitive
inspection interval to between 1,800
flight cycles and 3,000 flight cycles,
depending on the airplane group and
configuration. This service information
also adds an optional ultrasonic
inspection for the high frequency eddy
current inspection to detect cracking of
the critical fastener holes, and repairs if
necessary. This service information
adds procedures for repetitive detailed
inspections for cracking of the bulkhead
around the access door cutout and
around the critical fasteners in the
horizontal flange, and repair if
necessary. This service information also
provides an option, for certain
airplanes, to extend the repetitive
intervals by also doing repetitive
ultrasonic inspections for cracking of
the bulkhead around the fasteners in the
horizontal flange, and repairs if
necessary.
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 2008–05–10.
This proposed AD would reduce the
repetitive inspection interval, and add
repetitive detailed inspections for
cracking of the bulkhead, and repair if
necessary. This proposed AD would
also provide 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.
This proposed AD would also add an
option for the high frequency eddy
current inspection for cracking of the
critical fastener holes, and repair if
necessary.
Differences Between the Proposed AD
and the Service Information
Boeing Alert Service Bulletin 757–
54A0047, Revision 4, dated June 24,
2010, specifies to contact the
manufacturer for instructions on how to
repair certain conditions, but this
proposed AD would require repairing
those conditions in one of the following
ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) whom
we have authorized to make those
findings.
Change to Existing AD
We have removed the ‘‘Service
Bulletin Reference’’ paragraph from this
proposed AD. That paragraph was
identified as paragraph (f) in AD 2008–
05–10. Instead, we have provided the
full service bulletin citations throughout
this proposed AD and re-identified
subsequent paragraphs accordingly.
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
Labor cost
Part I Inspection on fasteners
and shims—vertical flange
[retained actions from existing AD].
Part II Inspection on fasteners—horizontal flange
[retained actions from existing AD].
Part IV inspection on critical
fasteners—horizontal flange
[retained actions from existing AD].
Part II Additional inspection
actions on fasteners—horizontal flange [new proposed
action].
Part IV inspection on critical
fasteners—horizontal flange
[new proposed action].
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Action
28 work-hours × $85 per hour
= $2,380 per inspection
cycle.
$0
$2,380 per inspection cycle ...
$735,420 per inspection cycle.
6 work-hours × $85 per hour
= $510 per inspection cycle.
0
$510 per inspection cycle ......
$157,590 per inspection cycle.
6 work-hours × $85 per hour
= $510 per inspection cycle.
0
$510 per inspection cycle ......
$157,590 per inspection cycle.
10 work-hours × $85 per hour
= $850 per inspection cycle.
0
$850 per inspection cycle ......
$262,650 per inspection cycle.
8 to 22 work-hours × $85 per
hour = $680 to $1,870 per
inspection cycle.
0
$680 to $1,870 per inspection
cycle.
$210,120 to $577,830 per inspection cycle.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
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Parts cost
Cost per product
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
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Cost on U.S. operators
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
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Federal Register / Vol. 76, No. 164 / Wednesday, August 24, 2011 / Proposed Rules
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.
§ 39.13
[Amended]
2. The FAA amends § 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.
Comments Due Date
(a) The FAA must receive comments on
this AD action by October 11, 2011.
Affected ADs
(b) This AD supersedes AD 2008–05–10,
Amendment 39–15404.
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Applicability
(c) This AD applies to Boeing Model 757–
200, –200PF, and –200CB series airplanes;
certificated in any category; line numbers 1
through 1048 inclusive; powered by RollsRoyce engines.
Subject
(d) Joint Aircraft System Component
(JASC)/Air Transport Association (ATA) of
America Code 54, Nacelles/Pylons.
Unsafe Condition
(e) This AD was prompted by reports of
loose fasteners and cracks at the joint
common to the aft torque bulkhead and strutto-diagonal brace fitting and one report of
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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.
Compliance
(f) Comply with this AD within the
compliance times specified, unless already
done.
Restatement of the Requirements of AD
2007–16–13 With Reduced Repetitive
Intervals and New Optional Inspection
Method
One-Time Inspection and Repair With
Optional Inspection Method
(g) 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), 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 repairs, in accordance with Part IV
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 757–54A0047,
Revision 3, dated June 27, 2007; or Revision
4, dated June 24, 2010; except as required by
paragraph (k) of this AD. As of the effective
date of this AD, only Boeing Alert Service
Bulletin 757–54A0047, Revision 4, dated
June 24, 2010, may be used. 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, 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.
Repetitive Inspection and Repair
(h) 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) and (j) 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
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52903
the Accomplishment Instructions of Boeing
Alert Service Bulletin 757–54A0047,
Revision 4, dated June 24, 2010; except as
required by paragraph (k) of this AD. As of
the effective date of this AD, only Boeing
Alert Service Bulletin 757–54A0047,
Revision 4, dated June 24, 2010, may be used.
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 4, dated
June 24, 2010.
(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 4, dated
June 24, 2010; or within 90 days after the
effective date of this AD, whichever occurs
later.
Exceptions to Alert Service Bulletin
Procedures
(i) 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.
(j) 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.
(k) 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; or Revision
4, dated June 24, 2010; 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 (s) of this AD.
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Restatement of the Requirements of AD
2008–05–10
Inspection/Repair for Airplanes for Which
There Are No Conclusive Inspection Records
(l) 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 (l)(1) and
(l)(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), do the
actions specified in paragraph (g) of this AD,
except as required by paragraph (k) 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 (j) and (m)
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; except as
required by paragraph (k) of this AD. As of
the effective date of this AD, only Boeing
Alert Service Bulletin 757–54A0047,
Revision 4, dated June 24, 2010, may be used.
Repeat the actions specified in paragraph (h)
of this AD at the times specified in paragraph
(h)(4) of this AD.
Exception to Alert Service Bulletin
Procedures
(m) 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.
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Credit for Actions Done in Accordance With
Previous Service Information
(n) Except for the actions specified in
paragraph (l) of this AD, actions done before
March 18, 2008, in accordance with Boeing
Service Bulletin 757–54A0047, Revision 1,
dated March 24, 2005; or Boeing Alert
Service Bulletin 757–54A0047, Revision 2,
dated January 31, 2007; are considered
acceptable for compliance with the
corresponding actions specified in this AD.
(o) An inspection and corrective actions
done before June 29, 2005 (the effective date
of AD 2005–12–04), in accordance with
paragraph (b) or (c), as applicable, of AD
2004–12–07, are acceptable for compliance
with the initial inspection requirement of
paragraph (h) of this AD.
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An Acceptable Method of Compliance With
Certain Requirements of AD 2004–12–07
(p) Accomplishing the actions specified in
paragraphs (g) and (h) of this AD terminates
the requirements specified in paragraphs (b)
and (c) of AD 2004–12–07.
New Requirements of This AD
Repetitive Inspections and Repair
(q) At the applicable initial compliance
times specified in paragraph (r) of this AD:
Do the applicable actions specified in
paragraph (q)(1) or (q)(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. 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 Boeing Alert Service Bulletin 757–
54A0047, Revision 4, dated June 24, 2010. 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 (s) of this AD.
(1) For Group 1, Configuration 1 airplanes
identified in Boeing Alert Service Bulletin
757–54A0047, Revision 4, dated June 24,
2010: Do the actions specified in paragraph
(q)(1)(i) or (q)(1)(ii) of this AD.
(i) Do a detailed inspection for cracking of
the bulkhead and in the area around the
access door cutout and around the critical
fasteners in the horizontal flange.
(ii) Do detailed inspection for cracking of
the bulkhead and 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 (q) of
this AD.
(2) For Group 1, Configuration 2 airplanes;
and Group 2 airplanes; identified in Boeing
Alert Service Bulletin 757–54A0047,
Revision 4, dated June 24, 2010: Do a
detailed inspection for cracking of the
bulkhead and in the area around the access
door cutout and around the critical fasteners
in the horizontal flange.
(r) At the applicable times specified in
paragraphs (r)(1) and (r)(2) of this AD, do the
actions required by paragraph (q) of this AD.
(1) For Group 1, Configuration 1 airplanes
identified in Boeing Alert Service Bulletin
757–54A0047, Revision 4, dated June 24,
2010: At the later of the times specified in
paragraph (r)(1)(i) or (r)(1)(ii) of this AD.
(i) Within 1,800 flight cycles after
accomplishing the most recent inspection
required by paragraph (h) 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 4, dated June 24, 2010: At the later
of the times specified in paragraph (r)(2)(i) or
(r)(2)(ii) of this AD.
(i) Within 3,000 flight cycles after
accomplishing the most recent inspection
required by paragraph (h) of this AD.
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(ii) Within 90 days after the effective date
of this AD.
Alternative Methods of Compliance
(AMOCs)
(s)(1) The Manager, Seattle 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 e-mailed 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.
(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 are
approved as AMOCs for the corresponding
provisions of this AD.
(5) AMOCs approved previously in
accordance with AD 2005–12–04 are
approved as AMOCs for the corresponding
provisions of this AD.
(6) AMOCs approved previously in
accordance with AD 2007–16–13 are
approved as AMOCs for the corresponding
provisions of this AD.
(7) AMOCs approved previously in
accordance with AD 2008–05–10 are
approved as AMOCs for the corresponding
provisions of this AD.
Related Information
(t) 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; e-mail: Nancy.Marsh@faa.gov.
(u) 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; e-mail: me.boecom@boeing.com;
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.
E:\FR\FM\24AUP1.SGM
24AUP1
Federal Register / Vol. 76, No. 164 / Wednesday, August 24, 2011 / Proposed Rules
Issued in Renton, Washington, on August
12, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
Comments Invited
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
This action proposes to
modify Salt Lake City, UT, Class B
airspace to contain aircraft conducting
Instrument Flight Rules (IFR)
instrument approach procedures to Salt
Lake City International Airport (SCL),
Salt Lake City, UT. The FAA is taking
this action to improve the flow of air
traffic, enhance safety, and reduce the
potential for midair collision, while
accommodating the concerns of airspace
users. Further, this effort supports the
FAA’s national airspace redesign goal of
optimizing terminal and en route
airspace to reduce aircraft delays and
improve system capacity.
DATES: Comments must be received on
or before October 24, 2011.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, M–
30, 1200 New Jersey Avenue, SE., West
Building Ground Floor, Room W12–140,
Washington, DC 20590–0001; telephone:
(202) 366–9826. You must identify FAA
Docket No. FAA–2011–0438 and
Airspace Docket No. 11–AWA–4 at the
beginning of your comments. You may
also submit comments through the
Internet at http:
//www.regulations.gov.
FOR FURTHER INFORMATION CONTACT:
Colby Abbott, Airspace, Regulations,
and ATC Procedures Group, Office of
Airspace Services, Federal Aviation
Administration, 800 Independence
Avenue, SW., Washington, DC 20591;
telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers (FAA Docket No. FAA–
2011–0438 and Airspace Docket No. 11–
AWA–4) and be submitted in triplicate
to the Docket Management Facility (see
ADDRESSES section for address and
phone number). You may also submit
comments through the Internet at https://
www.regulations.gov.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this action must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket Nos. FAA–2011–0438 and
Airspace Docket No. 11–AWA–4.’’ The
postcard will be date/time stamped and
returned to the commenter.
All communications received on or
before the specified closing date for
comments will be considered before
taking action on the proposed rule. The
proposal contained in this action may
be changed in light of comments
received. All comments submitted will
be available for examination in the
public docket both before and after the
closing date for comments. A report
summarizing each substantive public
contact with FAA personnel concerned
with this rulemaking will be filed in the
docket.
Availability of NPRMs
[FR Doc. 2011–21668 Filed 8–23–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2011–0438; Airspace
Docket No. 11–AWA–4]
RIN 2120–AA66
Proposed Amendment to Class B
Airspace; Salt Lake City, UT
AGENCY:
wreier-aviles on DSKGBLS3C1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
16:47 Aug 23, 2011
Jkt 223001
An electronic copy of this document
may be downloaded through the
Internet at https://www.regulations.gov.
Recently published rulemaking
documents can also be accessed through
the FAA’s Web page at https://
www.faa.gov/regulations_policies/
rulemaking/recently_published/.
You may review the public docket
containing the proposal, any comments
received and any final disposition in
person in the Dockets Office (see
ADDRESSES section for address and
phone number) between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. An informal docket
may also be examined during normal
business hours at the office of the
Western Service Center, Federal
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
52905
Aviation Administration, 1601 Lind
Ave., SW., Renton, WA 98057.
Persons interested in being placed on
a mailing list for future NPRMs should
contact the FAA’s Office of Rulemaking,
(202) 267–9677, for a copy of Advisory
Circular No. 11–2A, Notice of Proposed
Rulemaking Distribution System, which
describes the application procedure.
Background
In 1989, the FAA issued a final rule
establishing the Salt Lake City, UT,
Terminal Control Area (54 FR 43786).
As a result of the Airspace
Reclassification final rule (56 FR 65638),
which became effective in 1993, the
terms ‘‘terminal control area’’ and
‘‘airport radar service area’’ were
replaced by ‘‘Class B airspace area’’ and
‘‘Class C airspace area,’’ respectively.
The primary purpose of a Class B
airspace area is to reduce the potential
for midair collisions in the airspace
surrounding airports with high-density
air traffic operations by providing an
area in which all aircraft are subject to
certain operating rules and equipment
requirements.
The SLC Class B airspace area was
last modified in 1995 (60 FR 48350)
using air traffic activity levels from the
1990s, and has not been modified since.
In recent years, Salt Lake City has
completed construction projects to
modernize, enhance safety, and provide
for increased capacity at SLC. These
projects included the construction of a
new Runway 16 R/34 L at SLC. The new
west runway places departures closer to
the Oquirrh Mountains southwest of
SLC, and these departures need to climb
to 10,000 feet to safely clear the terrain.
This requires downwind traffic to level
at 11,000 feet to remain above
departures, which leaves the arrival
aircraft outside the Class B airspace.
Since the SLC Class B airspace area
was established, SLC has experienced
increased traffic levels, a considerably
different fleet mix, and airport
infrastructure improvements enabling
simultaneous instrument approach
procedures. For calendar year 2009, SLC
documented 328,508 total operations
and was rated 24th among all
Commercial Service Airports with
9,903,821 passenger enplanements.
Under the current Class B airspace
configuration, aircraft routinely enter,
exit, and then reenter Class B airspace
while flying published instrument
approach procedures, which is contrary
to FAA Orders. Modeling of existing
traffic flows has shown that the
proposed expanded Class B airspace
would enhance safety by containing all
instrument approach procedures, and
associated traffic patterns, within the
E:\FR\FM\24AUP1.SGM
24AUP1
Agencies
[Federal Register Volume 76, Number 164 (Wednesday, August 24, 2011)]
[Proposed Rules]
[Pages 52901-52905]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-21668]
-----------------------------------------------------------------------
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 Model 757-200, -
200PF, and -200CB Series 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 the products listed above. The existing AD
currently requires repetitive inspections of the shim installation
between the engine strut vertical flange and bulkhead, and repair if
necessary. The existing AD also requires, for certain airplanes, an
inspection for cracking of the four critical fastener holes in the
horizontal flange, and repair if necessary. Additionally, the existing
AD requires that the existing action be performed on airplanes without
conclusive records of previous inspections. Since we issued that AD, we
have received 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 proposed AD would reduce the repetitive
inspection interval, and add repetitive detailed inspections for
cracking of the bulkhead, and repair if necessary. This proposed AD
would also provide 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. This proposed AD
would also add an option for the high frequency eddy current inspection
for cracking of the critical fastener holes, and repair if necessary.
We are proposing 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.
DATES: We must receive comments on this proposed AD by October 11,
2011.
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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data & Services Management, P.O. Box
3707, MC 2H-65, Seattle, Washington 98124-2207; phone: 206-544-5000,
extension 1; fax: 206-766-5680; e-mail: me.boecom@boeing.com; Internet:
https://www.myboeingfleet.com. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at 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: 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; e-mail: Nancy.Marsh@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-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 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 February 22, 2008, we issued AD 2008-05-10, Amendment 39-15404
(73 FR 11347, March 3, 2008), for certain Boeing Model 757-200, -200PF,
and -200CB series airplanes powered by Rolls-Royce engines. That AD
requires repetitive inspections of the shim installation between the
engine strut vertical flange and bulkhead, and repair if necessary.
That AD also requires, for certain airplanes, an inspection for
cracking of the four critical fastener holes in the horizontal flange,
and repair if necessary. That AD resulted from reports of cracking in
the pylon under bolts that appear to be undamaged during the existing
AD inspections. That AD also resulted from our determination that
operators did not maintain records of previous inspections that are
necessary to determine the appropriate corrective actions. We issued
that 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.
Actions Since Existing AD Was Issued
Since we issued AD 2008-05-10, we have received 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
[[Page 52902]]
such damage found fewer than 3,000 flight cycles after the last
inspection.
Related Service Information
We reviewed Boeing Alert Service Bulletin 757-54A0047, Revision 4,
dated June 24, 2010. This service information reduces the repetitive
inspection interval to between 1,800 flight cycles and 3,000 flight
cycles, depending on the airplane group and configuration. This service
information also adds an optional ultrasonic inspection for the high
frequency eddy current inspection to detect cracking of the critical
fastener holes, and repairs if necessary. This service information adds
procedures for repetitive detailed inspections for cracking of the
bulkhead around the access door cutout and around the critical
fasteners in the horizontal flange, and repair if necessary. This
service information also provides an option, for certain airplanes, to
extend the repetitive intervals by also doing repetitive ultrasonic
inspections for cracking of the bulkhead around the fasteners in the
horizontal flange, and repairs if necessary.
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 2008-05-
10.
This proposed AD would reduce the repetitive inspection interval,
and add repetitive detailed inspections for cracking of the bulkhead,
and repair if necessary. This proposed AD would also provide 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. This proposed AD would also add an option for the
high frequency eddy current inspection for cracking of the critical
fastener holes, and repair if necessary.
Differences Between the Proposed AD and the Service Information
Boeing Alert Service Bulletin 757-54A0047, Revision 4, dated June
24, 2010, specifies to contact the manufacturer for instructions on how
to repair certain conditions, but this proposed AD would require
repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Change to Existing AD
We have removed the ``Service Bulletin Reference'' paragraph from
this proposed AD. That paragraph was identified as paragraph (f) in AD
2008-05-10. Instead, we have provided the full service bulletin
citations throughout this proposed AD and re-identified subsequent
paragraphs accordingly.
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
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Part I Inspection on fasteners and 28 work-hours x $85 per $0 $2,380 per inspection $735,420 per inspection cycle.
shims--vertical flange [retained hour = $2,380 per cycle.
actions from existing AD]. inspection cycle.
Part II Inspection on fasteners-- 6 work-hours x $85 per 0 $510 per inspection $157,590 per inspection cycle.
horizontal flange [retained actions hour = $510 per cycle.
from existing AD]. inspection cycle.
Part IV inspection on critical 6 work-hours x $85 per 0 $510 per inspection $157,590 per inspection cycle.
fasteners--horizontal flange hour = $510 per cycle.
[retained actions from existing AD]. inspection cycle.
Part II Additional inspection actions 10 work-hours x $85 per 0 $850 per inspection $262,650 per inspection cycle.
on fasteners--horizontal flange [new hour = $850 per cycle.
proposed action]. inspection cycle.
Part IV inspection on critical 8 to 22 work-hours x $85 0 $680 to $1,870 per $210,120 to $577,830 per inspection cycle.
fasteners--horizontal flange [new per hour = $680 to inspection cycle.
proposed action]. $1,870 per inspection
cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or
[[Page 52903]]
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) 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.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
11, 2011.
Affected ADs
(b) This AD supersedes AD 2008-05-10, Amendment 39-15404.
Applicability
(c) This AD applies to Boeing Model 757-200, -200PF, and -200CB
series airplanes; certificated in any category; line numbers 1
through 1048 inclusive; powered by Rolls-Royce engines.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 54, Nacelles/Pylons.
Unsafe Condition
(e) 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.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Restatement of the Requirements of AD 2007-16-13 With Reduced
Repetitive Intervals and New Optional Inspection Method
One-Time Inspection and Repair With Optional Inspection Method
(g) 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), 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 repairs, in
accordance with Part IV of the Accomplishment Instructions of Boeing
Alert Service Bulletin 757-54A0047, Revision 3, dated June 27, 2007;
or Revision 4, dated June 24, 2010; except as required by paragraph
(k) of this AD. As of the effective date of this AD, only Boeing
Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010,
may be used. 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, 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.
Repetitive Inspection and Repair
(h) 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) and (j) 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; except as required by paragraph (k) of this
AD. As of the effective date of this AD, only Boeing Alert Service
Bulletin 757-54A0047, Revision 4, dated June 24, 2010, may be used.
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 4, dated June 24, 2010.
(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 4, dated June 24, 2010; or within 90
days after the effective date of this AD, whichever occurs later.
Exceptions to Alert Service Bulletin Procedures
(i) 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.
(j) 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.
(k) 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; or Revision 4, dated June 24, 2010; 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 (s) of this AD.
[[Page 52904]]
Restatement of the Requirements of AD 2008-05-10
Inspection/Repair for Airplanes for Which There Are No Conclusive
Inspection Records
(l) 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 (l)(1) and (l)(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), do the actions specified in paragraph (g) of this
AD, except as required by paragraph (k) 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 (j) and
(m) 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; except as required by
paragraph (k) of this AD. As of the effective date of this AD, only
Boeing Alert Service Bulletin 757-54A0047, Revision 4, dated June
24, 2010, may be used. Repeat the actions specified in paragraph (h)
of this AD at the times specified in paragraph (h)(4) of this AD.
Exception to Alert Service Bulletin Procedures
(m) 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.
Credit for Actions Done in Accordance With Previous Service Information
(n) Except for the actions specified in paragraph (l) of this
AD, actions done before March 18, 2008, in accordance with Boeing
Service Bulletin 757-54A0047, Revision 1, dated March 24, 2005; or
Boeing Alert Service Bulletin 757-54A0047, Revision 2, dated January
31, 2007; are considered acceptable for compliance with the
corresponding actions specified in this AD.
(o) An inspection and corrective actions done before June 29,
2005 (the effective date of AD 2005-12-04), in accordance with
paragraph (b) or (c), as applicable, of AD 2004-12-07, are
acceptable for compliance with the initial inspection requirement of
paragraph (h) of this AD.
An Acceptable Method of Compliance With Certain Requirements of AD
2004-12-07
(p) Accomplishing the actions specified in paragraphs (g) and
(h) of this AD terminates the requirements specified in paragraphs
(b) and (c) of AD 2004-12-07.
New Requirements of This AD
Repetitive Inspections and Repair
(q) At the applicable initial compliance times specified in
paragraph (r) of this AD: Do the applicable actions specified in
paragraph (q)(1) or (q)(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. 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 Boeing Alert Service Bulletin 757-54A0047,
Revision 4, dated June 24, 2010. 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 (s) of this AD.
(1) For Group 1, Configuration 1 airplanes identified in Boeing
Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010:
Do the actions specified in paragraph (q)(1)(i) or (q)(1)(ii) of
this AD.
(i) Do a detailed inspection for cracking of the bulkhead and in
the area around the access door cutout and around the critical
fasteners in the horizontal flange.
(ii) Do detailed inspection for cracking of the bulkhead and 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 (q) of this AD.
(2) For Group 1, Configuration 2 airplanes; and Group 2
airplanes; identified in Boeing Alert Service Bulletin 757-54A0047,
Revision 4, dated June 24, 2010: Do a detailed inspection for
cracking of the bulkhead and in the area around the access door
cutout and around the critical fasteners in the horizontal flange.
(r) At the applicable times specified in paragraphs (r)(1) and
(r)(2) of this AD, do the actions required by paragraph (q) of this
AD.
(1) For Group 1, Configuration 1 airplanes identified in Boeing
Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010:
At the later of the times specified in paragraph (r)(1)(i) or
(r)(1)(ii) of this AD.
(i) Within 1,800 flight cycles after accomplishing the most
recent inspection required by paragraph (h) 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 4, dated June 24, 2010: At the later of the times specified
in paragraph (r)(2)(i) or (r)(2)(ii) of this AD.
(i) Within 3,000 flight cycles after accomplishing the most
recent inspection required by paragraph (h) of this AD.
(ii) Within 90 days after the effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(s)(1) The Manager, Seattle 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 e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane and the approval must
specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 2004-12-07
are approved as AMOCs for the corresponding provisions of this AD.
(5) AMOCs approved previously in accordance with AD 2005-12-04
are approved as AMOCs for the corresponding provisions of this AD.
(6) AMOCs approved previously in accordance with AD 2007-16-13
are approved as AMOCs for the corresponding provisions of this AD.
(7) AMOCs approved previously in accordance with AD 2008-05-10
are approved as AMOCs for the corresponding provisions of this AD.
Related Information
(t) 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; e-mail:
Nancy.Marsh@faa.gov.
(u) 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; e-mail:
me.boecom@boeing.com; Internet: https://www.myboeingfleet.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
[[Page 52905]]
Issued in Renton, Washington, on August 12, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-21668 Filed 8-23-11; 8:45 am]
BILLING CODE 4910-13-P