[Federal Register Volume 78, Number 13 (Friday, January 18, 2013)]
[Rules and Regulations]
[Pages 4042-4047]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-00897]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0724; Directorate Identifier 2010-NM-181-AD;
Amendment 39-17299; AD 2012-26-04]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain The Boeing Company Model 757-200, -200PF, and -200CB series
airplanes powered by Rolls-Royce engines. That AD currently 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. This new AD reduces the repetitive
inspection interval; adds repetitive detailed inspections for cracking
of the bulkhead, and repair if necessary; allows an extension of the
repetitive intervals for certain airplanes by also doing repetitive
ultrasonic inspections for cracking of the bulkhead, and repair if
necessary; and provides an option for a high frequency eddy current
inspection for cracking of the critical fastener holes, and repair if
necessary. This action also adds a terminating action for certain
repetitive inspections. 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.
DATES: This AD is effective February 22, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of February 22,
2013.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of August
24, 2007 (72 FR 44753, August 9, 2007).
ADDRESSES: For service information identified in this 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 AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
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:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede airworthiness directive (AD) 2008-05-
10, Amendment 39-15404 (73 FR 11347, March 3, 2008). (AD 2008-05-10
superseded AD 2007-16-13, Amendment 39-15152 (72 FR 44753, August 9,
2007); and AD 2007-16-13 superseded AD 2005-12-04, Amendment 39-14120
(70 FR 34313, June 14, 2005).) AD 2008-05-10 applies to the specified
products. The SNPRM published in the Federal Register on June 21, 2012
(77 FR 37332). The original NPRM (76 FR 52901, August 24, 2011)
proposed to continue to require repetitive inspections of the shim
installation between the engine strut vertical flange and bulkhead, and
repair if necessary. That NPRM also proposed to continue to require,
for certain airplanes, inspecting 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, 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 add an option for a high frequency eddy
current inspection for cracking of the critical fastener holes, and
repair if necessary. The SNPRM proposed to add a terminating action for
certain repetitive inspections.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 37332, June 21, 2012) and the FAA's response to each comment.
[[Page 4043]]
Support for the SNPRM (77 FR 37332, June 21, 2012)
United Airlines (United) stated that it has 41 Model 757-200
airplanes affected by the SNPRM (77 FR 37332, June 21, 2012). United
stated that, in general, it concurs with the SNPRM to mandate the
inspections and modifications described in Boeing Alert Service
Bulletin 757-54A0047, Revision 5, dated June 9, 2011.
UPS stated that it concurs with the reduced inspection interval
specified in the SNPRM (77 FR 37332, June 21, 2012), as it provides
additional opportunity beyond that required by AD 2008-05-10, Amendment
39-15404 (73 FR 11347, March 3, 2008), to find and correct any damage.
Request To Change Compliance Time
United requested that we remove the 54-month compliance time in
favor of only a 9,000 airplane-cycle limit for the modification
specified in paragraph (o) of the SNPRM (77 FR 37332, June 21, 2012).
United stated that the 54-month compliance time does not align with
current 72-month heavy check intervals at United. United stated that it
understands the related bulkhead cracking to be a fatigue related
failure, thus negating the need for a calendar driven modification
limit. United stated it believes that the currently mandated repetitive
inspection limits, in conjunction with a 9,000-airplane-cycle mandated
modification limit only, would provide a safe program that would allow
for a controlled implementation that minimizes the negative financial
impact to operators.
We disagree with the request to change the specified compliance
time. We have determined that the 54-month compliance time (grace
period), as specified in Boeing Alert Service Bulletin 757-54A0047,
Revision 5, dated June 9, 2011, is necessary to adequately address the
identified unsafe condition. This structure has been the subject of AD
2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008); which
superseded AD 2007-16-13, Amendment 39-15152 (72 FR 44753, August 9,
2007); which superseded AD 2005-12-04, Amendment 39-14120 (70 FR 34313,
June 14, 2005). In each of these ADs, the results from the new
inspection found more damage than anticipated, and more frequent and
complicated inspections were needed.
In developing an appropriate compliance time for the modification
specified in paragraph (o) of this AD, we considered the safety
implications, the time necessary to design an acceptable modification,
and normal maintenance schedules for timely accomplishment of the
modification. In light of these items, we have determined that a 54-
month compliance time (grace period) is appropriate. However, under the
provisions of paragraph (q) of this AD, we will consider requests for
approval of an extension of the compliance time if sufficient data are
submitted to substantiate that the extension would provide an
acceptable level of safety. We have not changed the AD in this regard.
Request To Change Terminating Action
UPS requested that the terminating action proposed in the SNPRM (77
FR 37332, June 21, 2012) be optional in lieu of continued reduced
interval inspections, and the terminating action be required only if
the reduced interval inspections find cracks or other damage at the
fitting.
We do not agree to change the required terminating action specified
in this AD because this portion of the Model 757 pylon has been the
subject of AD 2008-05-10, Amendment 39-15404 (73 FR 11347, March 3,
2008); which superseded AD 2007-16-13, Amendment 39-15152 (72 FR 44753,
August 9, 2007); which superseded AD 2005-12-04, Amendment 39-14120 (70
FR 34313, June 14, 2005). In each of these ADs, results from the new,
more frequent, and more complicated inspections showed more damage than
anticipated. Under the provisions of paragraph (q) of this AD, we will
consider requests for approval of alternative methods of compliance
(AMOC) if sufficient data are submitted to substantiate that continued
inspections without the terminating action can mitigate the identified
unsafe condition. We have not changed the AD in this regard.
Request To Specify Certain Section of Service Information
Boeing requested that we specifically call out Part V of the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011, in paragraph (o) of the SNPRM
(77 FR 37332, June 21, 2012) to prevent misinterpretation in that
paragraph because it is different than all other locations in the
SNPRM.
We agree to specify Part V in paragraph (o) of this AD, as
requested by Boeing, since doing so will help prevent
misinterpretation. We have changed paragraph (o) of this AD to specify
PART V of the Accomplishment Instructions of Boeing Alert Service
Bulletin 757-54A0047, Revision 5, dated June 9, 2011.
Request To Change Paragraph Header
Boeing requested that we revise the header of paragraph (g) of the
SNPRM (77 FR 37332, June 21, 2012), by deleting ``With Reduced
Repetitive Intervals and New Optional Inspection Method.'' Boeing
stated that there are no repetitive inspection requirements in
paragraph (g) of the SNPRM.
We agree to modify the specified header, since the repetitive
inspection is specified in paragraph (h) of this AD. We have removed
the words ``Reduced Repetitive Intervals and New Optional Inspection
Interval'' from the header of paragraph (g) of this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously--and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM (77 FR 37332, June 21, 2012) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the SNPRM (77 FR 37332, June 21, 2012).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 309 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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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 4044]]
Part II inspection on fasteners-- 6 work-hours x $85 0 $510 per inspection $157,590 per
horizontal flange [retained per hour = $510 cycle. inspection cycle.
actions from AD 2008-05-10, per inspection
Amendment 39-15404 (73 FR 11347, cycle.
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 cycle. inspection cycle.
[retained action from AD 2008-05- per inspection
10, Amendment 39-15404 (73 FR cycle.
11347, March 3, 2008)].
Part II additional inspection on 10 work-hours x $85 0 $850 per inspection $262,650 per
fasteners--horizontal flange per hour = $850 cycle. inspection cycle.
[new action]. per inspection
cycle.
Part IV inspection on critical 8 to 22 work-hours 0 $680 to $1,870 per $210,120 to
fasteners--horizontal flange x $85 per hour = inspection cycle. $577,830 per
[new action]. $680 to $1,870 per inspection cycle.
inspection cycle.
Part V fastener replacement Up to 37 work-hours 750 Up to $3,895 per Up to $1,203,555
flange [new action]. x $85 per hour = strut. per 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 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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
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:
2012-26-04 The Boeing Company: Amendment 39-17299; Docket No. FAA-
2011-0724; Directorate Identifier 2010-NM-181-AD.
(a) Effective Date
This airworthiness directive (AD) is effective February 22,
2013.
(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
This paragraph restates the one-time inspection and repair
required by paragraph (g) of AD 2008-05-10, Amendment 39-15404 (73
FR 11347, March 3, 2008), with optional inspection method and
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
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
[[Page 4045]]
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 of 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 the actions
specified in 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 inspections 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 specified 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 specified in 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 and 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 Additional 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 March 18, 2008 (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 4046]]
(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 PART V of 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
performed 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 (which are not incorporated by reference in this AD).
(2) This paragraph provides credit for the initial inspection
required by paragraph (h) of this AD, if that inspection was
performed 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, 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 Boeing service information identified in this 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.
(s) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
February 22, 2013.
(i) Boeing Alert Service Bulletin 757-54A0047, Revision 4, dated
June 24, 2010.
(ii) Boeing Alert Service Bulletin 757-54A0047, Revision 5,
dated June 9, 2011.
(4) The following service information was approved for IBR on
August 24, 2007, (72 FR 44753, August 9, 2007).
(i) Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated
June 27, 2007.
(ii) Reserved.
(5) For Boeing service information identified in this 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.
[[Page 4047]]
(6) You may view this service information at 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.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton Washington, on December 17, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-00897 Filed 1-17-13; 8:45 am]
BILLING CODE 4910-13-P