Airworthiness Directives; The Boeing Company Airplanes, 75827-75831 [2012-30305]
Download as PDF
<![CDATA[
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations
Internet https://techpubs.services/messierdowty.com.
(4) You may review copies of the 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.
(5) 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 5, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–30370 Filed 12–21–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1228; Directorate
Identifier 2012–NM–190–AD; Amendment
39–17292; AD 2012–25–11]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
certain The Boeing Company Model
757–200, -200CB, and -300 series
airplanes. That AD currently requires
initial and repetitive inspections of the
fuselage skin and bear strap at the
forward, upper corner of the L1 entry
door cutout for cracking, and repair if
necessary. That action also provides an
optional terminating action for the
repetitive inspections. That AD also
requires additional inspections for
airplanes having repairs or preventative
modifications installed and inspections
for certain other airplanes. This AD
requires the previous actions with
additional airplane group configurations
added to paragraph (n) of this AD. This
AD was prompted by a determination
that certain airplane group
configurations in paragraph (n) of the
existing AD were inadvertently removed
in the final rule. We are issuing this AD
to detect and correct cracking of the
fuselage skin and bear strap at the
forward upper corner of the L1 entry
door cutout, which could result in
tkelley on DSK3SPTVN1PROD with
SUMMARY:
VerDate Mar<15>2010
04:58 Dec 22, 2012
Jkt 229001
reduced structural integrity of the L1
entry door, and consequent rapid
decompression of the airplane.
DATES: This AD is effective January 10,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 3, 2012 (77 FR 52212,
August 29, 2012).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of May 24, 2004 (69 FR
25481, May 7, 2004).
We must receive any comments on
this AD by February 11, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, 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, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206–
766–5680; Internet https://
www.myboeingfleet.com. You may
review copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, 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 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 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, FAA,
Seattle Aircraft Certification Office,
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
75827
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6440; fax:
425–917–6590; email:
nancy.marsh@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 23, 2012, we issued AD 2012–
15–15, Amendment 39–17144 (77 FR
52212, August 29, 2012), which
superseded AD 2004–09–32,
Amendment 39–13622 (69 FR 25481,
May 7, 2004), for certain The Boeing
Company Model 757–200, -200CB, and
-300 series airplanes. AD 2012–15–15
requires initial and repetitive
inspections of the fuselage skin and bear
strap at the forward, upper corner of the
L1 entry door cutout for cracking, and
repair if necessary. That action also
provides an optional terminating action
for the repetitive inspections. That AD
also requires additional inspections for
airplanes having repairs or preventative
modifications installed and inspections
for certain other airplanes. That AD
resulted from reports of additional
cracking in the fuselage skin. We issued
that AD to detect and correct cracking
of the fuselage skin and bear strap at the
forward upper corner of the L1 entry
door cutout, which could result in
reduced structural integrity of the L1
entry door, and consequent rapid
decompression of the airplane.
Actions Since AD Was Issued
Since we issued AD 2012–15–15,
Amendment 39–17144 (77 FR 52212,
August 29, 2012), it was noted that
certain airplane group configurations
included in paragraph (n) of the NPRM
were inadvertently removed in the final
rule. This AD includes Group 1,
Configuration 4, and Group 2,
Configuration 3, in paragraph (n) of this
AD.
FAA’s Determination
We are issuing 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.
AD Requirements
This AD requires retaining all
requirements of AD 2012–15–15,
Amendment 39–17144 (77 FR 52212,
August 29, 2012).
FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
E:\FR\FM\26DER1.SGM
26DER1
75828
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations
rule because all actions of AD 2012–15–
15, Amendment 39–17144 (77 FR
52212, August 29, 2012), are retained
and include certain airplane group
configurations in paragraph (n) of this
AD that were specified in the NPRM (76
FR 81890, December 29, 2011), but were
inadvertently removed in the final rule
of AD 2012–15–15. Therefore, we find
that notice and opportunity for prior
public comment are unnecessary and
that good cause exists for making this
amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include the docket number
FAA–2012–1228 and directorate
identifier 2012–NM–190–AD at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this 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 AD.
Costs of Compliance
We estimate that this AD affects 591
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Workhours
Action
Inspections (retained actions from existing AD 2012-15-15, Amendment
39-17144 (77 FR 52212, August 29,
2012)).
Inspection (retained actions from existing AD 2012–15–15, Amendment
39-17144 (77 FR 52212, August 29,
2012)).
Supplemental inspection (retained actions from existing AD 2012–15–15,
Amendment 39-17144 (77 FR
52212, August 29, 2012)).
Average
labor rate
per hour
Cost per airplane
Number of
U.S.registered
airplanes
Fleet cost
2
$85
$170 per inspection cycle .....
57
3
$85
$255 per inspection cycle .....
591
$150,705 per inspection cycle.
15
$85
$1,275 per inspection cycle ..
591
$753,525 per inspection cycle.
We estimate the following costs to do
any necessary repairs that would be
required based on the results of the
inspections. We have no way of
$9,690 per inspection cycle.
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per product
Up to 26 work-hours × $85 =
Up to $2,210.
Up to $2,661
Up to $4,871 depending on configuration.
18 work-hours × $85 = $1,530
$1,338 ..........
$2,868
Authority for This Rulemaking
tkelley on DSK3SPTVN1PROD with
Repair (retained actions from existing AD
2012-15–15, Amendment 39-17144 (77 FR
52212, August 29, 2012)).
Preventive modification (retained actions from
existing AD 2012–15–15, Amendment
39-17144 (77 FR 52212, August 29, 2012)).
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.
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
VerDate Mar<15>2010
04:58 Dec 22, 2012
Jkt 229001
Regulatory Findings
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
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
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.
E:\FR\FM\26DER1.SGM
26DER1
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations
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 part 39 of the Federal
Aviation Regulations (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)
2012–15–15, Amendment 39–17144 (77
FR 52212, August 29, 2012), and adding
the following new AD:
■
2012–25–11 The Boeing Company:
Amendment 39–17292; Docket No.
FAA–2012–1228; Directorate Identifier
2012–NM–190–AD.
(a) Effective Date
This AD is effective January 10, 2013.
(b) Affected ADs
This AD supersedes AD 2012–15–15,
Amendment 39–17144 (77 FR 52212, August
29, 2012).
(c) Applicability
This AD applies to all The Boeing
Company Model 757–200, -200CB, and -300
series airplanes, certificated in any category.
Model 757–200PF series airplanes are not
affected by this AD.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53: Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracks
in the fuselage skin and bear strap at the
forward upper corner of the L1 entry door
cutout. We are issuing this AD to detect and
correct cracking of the fuselage skin and bear
strap at the forward, upper corner of the L1
entry door cutout, which could result in
reduced structural integrity of the L1 entry
door and consequent rapid decompression of
the airplane.
tkelley on DSK3SPTVN1PROD with
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Initial Inspection With
Terminating Action
This paragraph restates the requirements of
paragraph (g) of AD 2012–15–15,
Amendment 39–17144 (77 FR 52212, August
29, 2012), with a terminating action. For
airplanes having line numbers 1 through 90
VerDate Mar<15>2010
04:58 Dec 22, 2012
Jkt 229001
inclusive: Within 500 flight cycles after May
24, 2004 (the effective date of AD 2004–09–
32, Amendment 39–13622 (69 FR 25481, May
7, 2004)), or within 90 days after May 24,
2004 (the effective date of AD 2004–09–32),
whichever occurs later, do the inspections of
the forward upper corner of the L1 entry door
cutout specified in paragraphs (g)(1), (g)(2),
and (g)(3) of this AD, per Part 1 of the Work
Instructions of Boeing Special Attention
Service Bulletin 757–53–0089, dated March
18, 2004, until the initial inspection required
by paragraph (k) of this AD has been done.
Doing the repair specified in paragraph (i) or
(l) of this AD, or doing the preventive
modification specified in paragraph (j) of this
AD, terminates the inspections required by
this paragraph.
(1) Do a high frequency eddy current
(HFEC) inspection for cracking of the
fuselage skin around the adjacent fasteners.
(2) Do an HFEC inspection for cracking
along the edge of the skin and bear strap.
(3) Do a low frequency eddy current (LFEC)
inspection for cracking of the bear strap
around each fastener.
(h) Retained Repetitive Inspections and
Terminating Modification When No Crack Is
Detected
This paragraph restates the requirements of
paragraph (h) of AD 2012–15–15,
Amendment 39–17144 (77 FR 52212, August
29, 2012), with a terminating modification. If
no crack is detected during any inspection
required by paragraph (g) of this AD: Repeat
the inspections required by paragraph (g) of
this AD at intervals not to exceed 1,400 flight
cycles, until the requirements of paragraph
(k) of this AD are done. Doing the repair
specified in paragraph (i) or (l) of this AD,
or doing the preventive modification
specified in paragraph (j) of this AD, as
applicable, terminates the repetitive
inspections required by this paragraph.
(i) Retained Repair, With Repair Option
When Any Crack Is Detected
This paragraph restates the requirements of
paragraph (i) of AD 2012–15–15, Amendment
39–17144 (77 FR 52212, August 29, 2012),
with a repair option. If any crack is detected
during any inspection required by paragraph
(g) or (h) of this AD, and Boeing Special
Attention Service Bulletin 757–53–0089,
dated March 18, 2004, specifies to contact
Boeing for appropriate action: Before further
flight, repair, in accordance with a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or in
accordance with data meeting the type
certification basis of the airplane approved
by the Boeing Commercial Airplanes
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Seattle ACO, to make such
findings; or using a method approved in
accordance with the procedures specified in
paragraph (r) of this AD. For a repair method
to be approved, the approval must
specifically reference this AD. Doing the
repair terminates the inspections required by
paragraphs (g) and (h) of this AD.
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
75829
(j) Retained Optional Preventive
Modification
This paragraph restates the optional
preventive modification specified in
paragraph (j) of AD 2012–15–15, Amendment
39–17144 (77 FR 52212, August 29, 2012). As
an alternative to accomplishing the
inspections required by paragraphs (g) and
(h) of this AD, do the optional preventative
modification of the forward upper corner of
the L1 entry door cutout, and do all
applicable related investigative/corrective
actions, by accomplishing all the actions
specified in Part 2 of the Work Instructions
of Boeing Special Attention Service Bulletin
757–53–0089, dated March 18, 2004.
Accomplishment of the modification
constitutes terminating action for the
inspections required by paragraphs (g) and
(h) of this AD.
(k) Retained Inspections
This paragraph restates the requirements of
paragraph (k) of AD 2012–15–15,
Amendment 39–17144 (77 FR 52212, August
29, 2012). For airplanes in Group 1,
Configurations 1 and 2, and Group 2,
Configuration 1, as defined in Boeing Special
Attention Service Bulletin 757–53–0094,
Revision 1, dated August 12, 2009: Except as
provided by paragraph (p)(1) of this AD, at
the applicable times specified in paragraph
1.E, ‘‘Compliance,’’ of Boeing Special
Attention Service Bulletin 757–53–0094,
Revision 1, dated August 12, 2009, do HFEC
and LFEC inspections for cracking of the skin
and bear strap at the forward upper corner of
the L1 entry door cutout, in accordance with
the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 757–53–
0094, Revision 1, dated August 12, 2009,
except as provided by paragraph (p) of this
AD. Repeat the inspections thereafter at
intervals not to exceed 1,400 flight cycles.
Doing the initial inspection required by this
paragraph terminates the inspections
required by paragraphs (g) and (h) of this AD.
Doing the repair specified in paragraph (l) of
this AD, or doing the optional preventive
modification specified in paragraph (m) of
this AD, terminates the inspections required
by this paragraph.
(l) Retained Terminating Repair
This paragraph restates the terminating
repair specified in paragraph (l) of AD 2012–
15–15, Amendment 39–17144 (77 FR 52212,
August 29, 2012). If any cracking is found
during any inspection required by paragraph
(k) of this AD, before further flight, repair in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 757–53–0094, Revision 1,
dated August 12, 2009, except as required by
paragraph (p) of this AD. Doing the repair
terminates the repetitive inspections required
by paragraph (k) of this AD.
(m) Retained Optional Preventive
Modification
This paragraph restates the optional
preventive modification specified in
paragraph (m) of AD 2012–15–15,
Amendment 39–17144 (77 FR 52212, August
29, 2012). Accomplishing the optional
preventive modification, in accordance with
E:\FR\FM\26DER1.SGM
26DER1
75830
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations
the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 757–53–
0094, Revision 1, dated August 12, 2009,
except as provided by paragraph (p) of this
AD, terminates the repetitive inspections
required by paragraph (k) of this AD.
(n) Retained Inspections and Repair With
New Airplane Group Configurations
This paragraph restates the requirements of
paragraph (n) of AD 2012–15–15,
Amendment 39–17144 (77 FR 52212, August
29, 2012), with new airplane group
configurations. For airplanes in Group 1,
Configurations 3, 4, and 5; and Group 2,
Configurations 2, 3, and 4; as identified in
Boeing Special Attention Service Bulletin
757–53–0094, Revision 1, dated August 12,
2009; with a repair doubler; a doubler and a
tripler; or a doubler, tripler, and quadrupler
installed; or with a preventive modification
doubler installed: At the applicable times
specified in paragraph 1.E, ‘‘Compliance,’’ of
Boeing Special Attention Service Bulletin
757–53–0094, Revision 1, dated August 12,
2009, except as required by paragraph (p)(2)
of this AD, do LFEC, HFEC, and detailed
inspections, as applicable, for cracking of the
doubler, tripler, quadrupler, skin, bear strap,
and inner chord strap, as applicable, in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 757–53–0094, Revision 1,
dated August 12, 2009. Repeat the
inspections thereafter at the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Special Attention Service Bulletin
757–53–0094, Revision 1, dated August 12,
2009.
tkelley on DSK3SPTVN1PROD with
(o) Retained Repair
This paragraph restates the requirements of
paragraph (o) of AD 2012–15–15,
Amendment 39–17144 (77 FR 52212, August
29, 2012). If any cracking is found during any
inspection required by paragraph (n) of this
AD, before further flight, repair the crack in
accordance with the procedures specified in
paragraph (r) of this AD.
(p) Retained Exceptions to Service Bulletin
Specifications
This paragraph restates the exceptions
specified in paragraph (p) of AD 2012–15–15,
Amendment 39–17144 (77 FR 52212, August
29, 2012). The following exceptions apply to
this AD.
(1) Where Boeing Special Attention Service
Bulletin 757–53–0094, Revision 1, dated
August 12, 2009, specifies a compliance time
after the ‘‘original issue date’’ or ‘‘Revision 1
date of the service bulletin,’’ this AD requires
compliance within the specified compliance
time after October 3, 2012 (the effective date
of AD 2012–15–15, Amendment 39–17144
(77 FR 52212, August 29, 2012)).
(2) Where Boeing Special Attention Service
Bulletin 757–53–0094, Revision 1, dated
August 12, 2009, specifies doing the HFEC,
LFEC, and detailed inspections required by
paragraph (n) of this AD before the
accumulation of 37,500 total flight cycles,
this AD requires the inspections to be
accomplished at the latest of the times
specified in paragraphs (p)(2)(i), (p)(2)(ii),
and (p)(2)(iii) of this AD.
VerDate Mar<15>2010
04:58 Dec 22, 2012
Jkt 229001
(i) Before the accumulation of 37,500 total
flight cycles.
(ii) Within 24 months after October 3, 2012
(the effective date of AD 2012–15–15,
Amendment 39–17144 (77 FR 52212, August
29, 2012)).
(iii) Within 4,000 flight cycles since
installation of a repair doubler; a doubler and
a tripler; or a doubler, tripler, and
quadrupler; or on which a preventive
modification doubler is installed; in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 757–53–0094, Revision 1,
dated August 12, 2009; or in accordance with
paragraph (h) of this AD.
(3) Where Boeing Special Attention Service
Bulletin 757–53–0094, Revision 1, dated
August 12, 2009, specifies contacting Boeing
for repair instructions, this AD requires
repairing in accordance with the procedures
specified in paragraph (r) of this AD.
(4) Where Boeing Special Attention Service
Bulletin 757–53–0094, Revision 1, dated
August 12, 2009, specifies a specific fastener
and material to be used for accomplishing a
repair, this AD allows the substitution of
fastener and material, as specified in Chapter
51 of the Boeing 757 Structural Repair
Manual.
(5) Where Boeing Special Attention Service
Bulletin 757–53–0094, Revision 1, dated
August 12, 2009, specifies a specific fastener
grip length, this AD allows substitution of a
fastener grip length, as specified in Chapter
51 of the Boeing 757 Structural Repair
Manual.
(6) If it is necessary to remove more parts
for access, those parts may be removed. If
access is possible without removing
identified parts, it is not necessary to remove
all of the identified parts.
(q) Retained Credit for Previous Actions
This paragraph restates the credit
provisions specified in paragraph (q) of AD
2012–15–15, Amendment 39–17144 (77 FR
52212, August 29, 2012). For airplanes in
Group 1, Configurations 1 and 2; and Group
2, Configuration 1; as defined in Boeing
Special Attention 757–53–0094, Revision 1,
dated August 12, 2009: This paragraph
provides credit for the actions required by
paragraph (k) of this AD, if those actions
were performed before October 3, 2012 (the
effective date of AD 2012–15–15), using
Boeing Special Attention Service Bulletin
757–53–0094, dated January 16, 2008; or
Boeing Special Attention Service Bulletin
757–53–0089, dated March 18, 2004 (which
are not incorporated by reference in this AD).
(r) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the ACO, send it to ATTN: Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM–
120S, FAA, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6440; fax:
425–917–6432; email: nancy.marsh@faa.gov.
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
(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 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 previously approved in
accordance with AD 2004–09–32,
Amendment 39–13622 (69 FR 25481, May 7,
2004), are approved as AMOCs for the
corresponding actions specified in
paragraphs (g), (h), and (i) of this AD.
(5) AMOCs previously approved in
accordance with AD 2012–15–15,
Amendment 39–17144 (77 FR 52212, August
29, 2012)), are approved as AMOCs for the
corresponding actions specified in this AD.
(s) Related Information
(1) For more information about this AD,
contact Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, 1601
Lind Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6440; fax: 425–917–6432;
email: nancy.marsh@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(t) 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 October 3, 2012 (77 FR
52212, August 29, 2012).
(i) Boeing Special Attention Service
Bulletin 757–53–0094, Revision 1, dated
August 12, 2009.
(ii) Reserved.
(4) The following service information was
approved for IBR on May 24, 2004 (69 FR
25481, May 7, 2004).
(i) Boeing Special Attention Service
Bulletin 757–53–0089, dated March 18, 2004.
(ii) Reserved.
(5) 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; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(6) You may review copies of the 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.
(7) You may also review copies of the
service information that is incorporated by
E:\FR\FM\26DER1.SGM
26DER1
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations
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: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Renton, Washington, on
December 5, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–30305 Filed 12–21–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1198; Directorate
Identifier 2012–NE–35–AD; Amendment 39–
17289; AD 2012–25–08]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
tkelley on DSK3SPTVN1PROD with
Examining the AD Docket
We are adopting a new
airworthiness directive (AD) for certain
serial numbers (S/Ns) of Rolls-Royce plc
(RR) RB211-Trent 768–60, 772–60, and
772B–60 turbofan engines. This AD
requires initial and repetitive on-wing
or in-shop inspections of the high
pressure/intermediate pressure (HP/IP)
turbine bearing support oil feed tube
outer heat shield. This AD also requires
installation of a revised HP/IP turbine
bearing support structure as terminating
action to the repetitive inspections of
the HP/IP turbine bearing support oil
feed tube outer heat shield. This AD was
prompted by a report of high oil
consumption due to an oil leak from the
HP/IP turbine bearing support oil feed
tube. We are issuing this AD to prevent
failure of the HP turbine disc,
uncontained engine failure, and damage
to the airplane.
DATES: This AD becomes effective
January 10, 2013.
We must receive comments on this
AD by February 11, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication as of January 10,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications as of
December 14, 2007 (72 FR 67568,
November 29, 2007).
SUMMARY:
VerDate Mar<15>2010
04:58 Dec 22, 2012
Jkt 229001
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: U.S. Department of
Transportation, 1200 New Jersey
Avenue SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: 202–493–2251.
For service information identified in
this AD, contact Rolls-Royce plc,
Corporate Communications, P.O. Box
31, Derby, England, DE248BJ, phone:
011–44–1332–242424; fax: 011–44–
1332–245418, or email: https://
www.rolls-royce.com/contact/
civil_team.jsp. You may view this
service information at the FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803.
For information on the availability of
this material at the FAA, call 781–238–
7125.
ADDRESSES:
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (phone:
800–647–5527) is the same as the Mail
address provided in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Robert Morlath, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238 7154; fax: 781–238
7199; email: robert.c.morlath@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD 2012–
0201, dated September 26, 2012
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
In August 2011, a Trent 700 engine was
removed for high oil consumption, which
was found to have been caused by a small
hole in the oil feed tube of the High Pressure/
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
75831
Intermediate Pressure (HP/IP) Bearing
Support. The hole was the result of frettage
(chafing) with a fractured outer heat shield.
This is a known problem and recognized
unsafe condition that has re-emerged having
been previously addressed by EASA AD
2007–0260R1.
Investigation by RR revealed a build error
that, in contradiction to the build records, the
previous configuration of outer heat shield
(Pre-Service Bulletin (SB) 72–F117 standard)
was fitted on the oil feed tube service pipe
of the HP/IP structure. As the build error may
have been reproduced several times, it is
assumed that further post-SB 72–F117
standard structures may be in service with
pre-SB 72–F117 outer heat shields fitted to
the oil feed tube.
The frettage on the oil feed tube within the
HP/IP turbine bearings support structure
results from contact with the fracture edges
of the tubes outermost heat shield, which has
been found to fracture under thermal cycling
and then to chafe against the oil tube with
the potential to cause holes and consequent
oil leaks.
You may obtain further information
by examining the MCAI in the AD
docket.
On November 20, 2007, we issued AD
2007–24–09 (72 FR 67568, November
29, 2007) which corresponds with
EASA AD 2007–0260R1. Our AD has a
mandatory terminating action date of
May 31, 2010, however, there were, and
currently are, no U.S. operators of the
engines affected by those ADs. Those
ADs are only applicable to engines that
do not incorporate Modification
Standard 72–F117. Since those ADs
were issued, EASA has issued AD 2012–
0201 that is applicable to a specific set
of engines that may have had
Modification Standard 72–F117
incorporated incorrectly. EASA did not
supersede EASA AD 2007–0260R1 with
EASA AD 2012–0201 because EASA AD
2012–0201 only affects a very specific
population of engines that, having
incorporated Modification Standard 72–
F117, either correctly or incorrectly, are
no longer affected by EASA AD 2007–
0260R1. We are issuing our AD as a
standalone document for the same
reasons. This new AD also is applicable
only to the engines specified in the
MCAI, none of which are currently
registered to U.S. operators. Also, this
new AD lists certain service bulletins
that were previously incorporated by
reference in AD 2007–24–09.
Relevant Service Information
RR has issued Alert Service Bulletin
No. RB.211–72–AG873, dated February
27, 2012. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
E:\FR\FM\26DER1.SGM
26DER1
]]>Agencies
[Federal Register Volume 77, Number 247 (Wednesday, December 26, 2012)]
[Rules and Regulations]
[Pages 75827-75831]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-30305]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1228; Directorate Identifier 2012-NM-190-AD;
Amendment 39-17292; AD 2012-25-11]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain The Boeing Company Model 757-200, -200CB, and -300 series
airplanes. That AD currently requires initial and repetitive
inspections of the fuselage skin and bear strap at the forward, upper
corner of the L1 entry door cutout for cracking, and repair if
necessary. That action also provides an optional terminating action for
the repetitive inspections. That AD also requires additional
inspections for airplanes having repairs or preventative modifications
installed and inspections for certain other airplanes. This AD requires
the previous actions with additional airplane group configurations
added to paragraph (n) of this AD. This AD was prompted by a
determination that certain airplane group configurations in paragraph
(n) of the existing AD were inadvertently removed in the final rule. We
are issuing this AD to detect and correct cracking of the fuselage skin
and bear strap at the forward upper corner of the L1 entry door cutout,
which could result in reduced structural integrity of the L1 entry
door, and consequent rapid decompression of the airplane.
DATES: This AD is effective January 10, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 3,
2012 (77 FR 52212, August 29, 2012).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of May
24, 2004 (69 FR 25481, May 7, 2004).
We must receive any comments on this AD by February 11, 2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, 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, WA 98124-2207; telephone 206-544-5000,
extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
You may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 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 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 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, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6440; fax:
425-917-6590; email: nancy.marsh@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 23, 2012, we issued AD 2012-15-15, Amendment 39-17144 (77
FR 52212, August 29, 2012), which superseded AD 2004-09-32, Amendment
39-13622 (69 FR 25481, May 7, 2004), for certain The Boeing Company
Model 757-200, -200CB, and -300 series airplanes. AD 2012-15-15
requires initial and repetitive inspections of the fuselage skin and
bear strap at the forward, upper corner of the L1 entry door cutout for
cracking, and repair if necessary. That action also provides an
optional terminating action for the repetitive inspections. That AD
also requires additional inspections for airplanes having repairs or
preventative modifications installed and inspections for certain other
airplanes. That AD resulted from reports of additional cracking in the
fuselage skin. We issued that AD to detect and correct cracking of the
fuselage skin and bear strap at the forward upper corner of the L1
entry door cutout, which could result in reduced structural integrity
of the L1 entry door, and consequent rapid decompression of the
airplane.
Actions Since AD Was Issued
Since we issued AD 2012-15-15, Amendment 39-17144 (77 FR 52212,
August 29, 2012), it was noted that certain airplane group
configurations included in paragraph (n) of the NPRM were inadvertently
removed in the final rule. This AD includes Group 1, Configuration 4,
and Group 2, Configuration 3, in paragraph (n) of this AD.
FAA's Determination
We are issuing 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.
AD Requirements
This AD requires retaining all requirements of AD 2012-15-15,
Amendment 39-17144 (77 FR 52212, August 29, 2012).
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this
[[Page 75828]]
rule because all actions of AD 2012-15-15, Amendment 39-17144 (77 FR
52212, August 29, 2012), are retained and include certain airplane
group configurations in paragraph (n) of this AD that were specified in
the NPRM (76 FR 81890, December 29, 2011), but were inadvertently
removed in the final rule of AD 2012-15-15. Therefore, we find that
notice and opportunity for prior public comment are unnecessary and
that good cause exists for making this amendment effective in less than
30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the docket number FAA-2012-1228 and directorate identifier 2012-NM-190-
AD at the beginning of your comments. We specifically invite comments
on the overall regulatory, economic, environmental, and energy aspects
of this AD. We will consider all comments received by the closing date
and may amend this 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 AD.
Costs of Compliance
We estimate that this AD affects 591 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Work- Average U.S.-
Action hours labor rate Cost per airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections (retained actions from 2 $85 $170 per inspection cycle 57 $9,690 per inspection cycle.
existing AD 2012[dash]15[dash]15,
Amendment 39[dash]17144 (77 FR 52212,
August 29, 2012)).
Inspection (retained actions from 3 $85 $255 per inspection cycle 591 $150,705 per inspection cycle.
existing AD 2012-15-15, Amendment
39[dash]17144 (77 FR 52212, August 29,
2012)).
Supplemental inspection (retained 15 $85 $1,275 per inspection 591 $753,525 per inspection cycle.
actions from existing AD 2012-15-15, cycle.
Amendment 39[dash]17144 (77 FR 52212,
August 29, 2012)).
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the inspections. We have no
way of determining the number of aircraft that might need these
repairs:
On-condition Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
--------------------------------------------------------------------------------------------------------------------------------------------------------
Repair (retained actions from Up to 26 work-hours x $85 Up to $2,661.......... Up to $4,871 depending on configuration.
existing AD 2012[dash]15-15, = Up to $2,210.
Amendment 39[dash]17144 (77 FR
52212, August 29, 2012)).
Preventive modification (retained 18 work-hours x $85 = $1,338................ $2,868
actions from existing AD 2012-15-15, $1,530.
Amendment 39[dash]17144 (77 FR
52212, August 29, 2012)).
--------------------------------------------------------------------------------------------------------------------------------------------------------
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
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.
[[Page 75829]]
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 part 39 of the Federal Aviation
Regulations (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)
2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012), and
adding the following new AD:
2012-25-11 The Boeing Company: Amendment 39-17292; Docket No. FAA-
2012-1228; Directorate Identifier 2012-NM-190-AD.
(a) Effective Date
This AD is effective January 10, 2013.
(b) Affected ADs
This AD supersedes AD 2012-15-15, Amendment 39-17144 (77 FR
52212, August 29, 2012).
(c) Applicability
This AD applies to all The Boeing Company Model 757-200, -200CB,
and -300 series airplanes, certificated in any category. Model 757-
200PF series airplanes are not affected by this AD.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53: Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracks in the fuselage skin
and bear strap at the forward upper corner of the L1 entry door
cutout. We are issuing this AD to detect and correct cracking of the
fuselage skin and bear strap at the forward, upper corner of the L1
entry door cutout, which could result in reduced structural
integrity of the L1 entry door and consequent rapid decompression of
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Initial Inspection With Terminating Action
This paragraph restates the requirements of paragraph (g) of AD
2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012), with
a terminating action. For airplanes having line numbers 1 through 90
inclusive: Within 500 flight cycles after May 24, 2004 (the
effective date of AD 2004-09-32, Amendment 39-13622 (69 FR 25481,
May 7, 2004)), or within 90 days after May 24, 2004 (the effective
date of AD 2004-09-32), whichever occurs later, do the inspections
of the forward upper corner of the L1 entry door cutout specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD, per Part 1 of the
Work Instructions of Boeing Special Attention Service Bulletin 757-
53-0089, dated March 18, 2004, until the initial inspection required
by paragraph (k) of this AD has been done. Doing the repair
specified in paragraph (i) or (l) of this AD, or doing the
preventive modification specified in paragraph (j) of this AD,
terminates the inspections required by this paragraph.
(1) Do a high frequency eddy current (HFEC) inspection for
cracking of the fuselage skin around the adjacent fasteners.
(2) Do an HFEC inspection for cracking along the edge of the
skin and bear strap.
(3) Do a low frequency eddy current (LFEC) inspection for
cracking of the bear strap around each fastener.
(h) Retained Repetitive Inspections and Terminating Modification When
No Crack Is Detected
This paragraph restates the requirements of paragraph (h) of AD
2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012), with
a terminating modification. If no crack is detected during any
inspection required by paragraph (g) of this AD: Repeat the
inspections required by paragraph (g) of this AD at intervals not to
exceed 1,400 flight cycles, until the requirements of paragraph (k)
of this AD are done. Doing the repair specified in paragraph (i) or
(l) of this AD, or doing the preventive modification specified in
paragraph (j) of this AD, as applicable, terminates the repetitive
inspections required by this paragraph.
(i) Retained Repair, With Repair Option When Any Crack Is Detected
This paragraph restates the requirements of paragraph (i) of AD
2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012), with
a repair option. If any crack is detected during any inspection
required by paragraph (g) or (h) of this AD, and Boeing Special
Attention Service Bulletin 757-53-0089, dated March 18, 2004,
specifies to contact Boeing for appropriate action: Before further
flight, repair, in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or in accordance
with data meeting the type certification basis of the airplane
approved by the Boeing Commercial Airplanes Organization Designation
Authorization (ODA) that has been authorized by the Manager, Seattle
ACO, to make such findings; or using a method approved in accordance
with the procedures specified in paragraph (r) of this AD. For a
repair method to be approved, the approval must specifically
reference this AD. Doing the repair terminates the inspections
required by paragraphs (g) and (h) of this AD.
(j) Retained Optional Preventive Modification
This paragraph restates the optional preventive modification
specified in paragraph (j) of AD 2012-15-15, Amendment 39-17144 (77
FR 52212, August 29, 2012). As an alternative to accomplishing the
inspections required by paragraphs (g) and (h) of this AD, do the
optional preventative modification of the forward upper corner of
the L1 entry door cutout, and do all applicable related
investigative/corrective actions, by accomplishing all the actions
specified in Part 2 of the Work Instructions of Boeing Special
Attention Service Bulletin 757-53-0089, dated March 18, 2004.
Accomplishment of the modification constitutes terminating action
for the inspections required by paragraphs (g) and (h) of this AD.
(k) Retained Inspections
This paragraph restates the requirements of paragraph (k) of AD
2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012). For
airplanes in Group 1, Configurations 1 and 2, and Group 2,
Configuration 1, as defined in Boeing Special Attention Service
Bulletin 757-53-0094, Revision 1, dated August 12, 2009: Except as
provided by paragraph (p)(1) of this AD, at the applicable times
specified in paragraph 1.E, ``Compliance,'' of Boeing Special
Attention Service Bulletin 757-53-0094, Revision 1, dated August 12,
2009, do HFEC and LFEC inspections for cracking of the skin and bear
strap at the forward upper corner of the L1 entry door cutout, in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 757-53-0094, Revision 1, dated August 12,
2009, except as provided by paragraph (p) of this AD. Repeat the
inspections thereafter at intervals not to exceed 1,400 flight
cycles. Doing the initial inspection required by this paragraph
terminates the inspections required by paragraphs (g) and (h) of
this AD. Doing the repair specified in paragraph (l) of this AD, or
doing the optional preventive modification specified in paragraph
(m) of this AD, terminates the inspections required by this
paragraph.
(l) Retained Terminating Repair
This paragraph restates the terminating repair specified in
paragraph (l) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212,
August 29, 2012). If any cracking is found during any inspection
required by paragraph (k) of this AD, before further flight, repair
in accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 757-53-0094, Revision 1, dated August 12,
2009, except as required by paragraph (p) of this AD. Doing the
repair terminates the repetitive inspections required by paragraph
(k) of this AD.
(m) Retained Optional Preventive Modification
This paragraph restates the optional preventive modification
specified in paragraph (m) of AD 2012-15-15, Amendment 39-17144 (77
FR 52212, August 29, 2012). Accomplishing the optional preventive
modification, in accordance with
[[Page 75830]]
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 757-53-0094, Revision 1, dated August 12, 2009, except as
provided by paragraph (p) of this AD, terminates the repetitive
inspections required by paragraph (k) of this AD.
(n) Retained Inspections and Repair With New Airplane Group
Configurations
This paragraph restates the requirements of paragraph (n) of AD
2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012), with
new airplane group configurations. For airplanes in Group 1,
Configurations 3, 4, and 5; and Group 2, Configurations 2, 3, and 4;
as identified in Boeing Special Attention Service Bulletin 757-53-
0094, Revision 1, dated August 12, 2009; with a repair doubler; a
doubler and a tripler; or a doubler, tripler, and quadrupler
installed; or with a preventive modification doubler installed: At
the applicable times specified in paragraph 1.E, ``Compliance,'' of
Boeing Special Attention Service Bulletin 757-53-0094, Revision 1,
dated August 12, 2009, except as required by paragraph (p)(2) of
this AD, do LFEC, HFEC, and detailed inspections, as applicable, for
cracking of the doubler, tripler, quadrupler, skin, bear strap, and
inner chord strap, as applicable, in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 757-53-0094, Revision 1, dated August 12, 2009. Repeat the
inspections thereafter at the applicable times specified in
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service
Bulletin 757-53-0094, Revision 1, dated August 12, 2009.
(o) Retained Repair
This paragraph restates the requirements of paragraph (o) of AD
2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012). If
any cracking is found during any inspection required by paragraph
(n) of this AD, before further flight, repair the crack in
accordance with the procedures specified in paragraph (r) of this
AD.
(p) Retained Exceptions to Service Bulletin Specifications
This paragraph restates the exceptions specified in paragraph
(p) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29,
2012). The following exceptions apply to this AD.
(1) Where Boeing Special Attention Service Bulletin 757-53-0094,
Revision 1, dated August 12, 2009, specifies a compliance time after
the ``original issue date'' or ``Revision 1 date of the service
bulletin,'' this AD requires compliance within the specified
compliance time after October 3, 2012 (the effective date of AD
2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012)).
(2) Where Boeing Special Attention Service Bulletin 757-53-0094,
Revision 1, dated August 12, 2009, specifies doing the HFEC, LFEC,
and detailed inspections required by paragraph (n) of this AD before
the accumulation of 37,500 total flight cycles, this AD requires the
inspections to be accomplished at the latest of the times specified
in paragraphs (p)(2)(i), (p)(2)(ii), and (p)(2)(iii) of this AD.
(i) Before the accumulation of 37,500 total flight cycles.
(ii) Within 24 months after October 3, 2012 (the effective date
of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29,
2012)).
(iii) Within 4,000 flight cycles since installation of a repair
doubler; a doubler and a tripler; or a doubler, tripler, and
quadrupler; or on which a preventive modification doubler is
installed; in accordance with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 757-53-0094, Revision 1,
dated August 12, 2009; or in accordance with paragraph (h) of this
AD.
(3) Where Boeing Special Attention Service Bulletin 757-53-0094,
Revision 1, dated August 12, 2009, specifies contacting Boeing for
repair instructions, this AD requires repairing in accordance with
the procedures specified in paragraph (r) of this AD.
(4) Where Boeing Special Attention Service Bulletin 757-53-0094,
Revision 1, dated August 12, 2009, specifies a specific fastener and
material to be used for accomplishing a repair, this AD allows the
substitution of fastener and material, as specified in Chapter 51 of
the Boeing 757 Structural Repair Manual.
(5) Where Boeing Special Attention Service Bulletin 757-53-0094,
Revision 1, dated August 12, 2009, specifies a specific fastener
grip length, this AD allows substitution of a fastener grip length,
as specified in Chapter 51 of the Boeing 757 Structural Repair
Manual.
(6) If it is necessary to remove more parts for access, those
parts may be removed. If access is possible without removing
identified parts, it is not necessary to remove all of the
identified parts.
(q) Retained Credit for Previous Actions
This paragraph restates the credit provisions specified in
paragraph (q) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212,
August 29, 2012). For airplanes in Group 1, Configurations 1 and 2;
and Group 2, Configuration 1; as defined in Boeing Special Attention
757-53-0094, Revision 1, dated August 12, 2009: This paragraph
provides credit for the actions required by paragraph (k) of this
AD, if those actions were performed before October 3, 2012 (the
effective date of AD 2012-15-15), using Boeing Special Attention
Service Bulletin 757-53-0094, dated January 16, 2008; or Boeing
Special Attention Service Bulletin 757-53-0089, dated March 18, 2004
(which are not incorporated by reference in this AD).
(r) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the ACO, send it to
ATTN: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM-120S,
FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6440; fax: 425-917-6432; email: nancy.marsh@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 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 previously approved in accordance with AD 2004-09-32,
Amendment 39-13622 (69 FR 25481, May 7, 2004), are approved as AMOCs
for the corresponding actions specified in paragraphs (g), (h), and
(i) of this AD.
(5) AMOCs previously approved in accordance with AD 2012-15-15,
Amendment 39-17144 (77 FR 52212, August 29, 2012)), are approved as
AMOCs for the corresponding actions specified in this AD.
(s) Related Information
(1) For more information about this AD, contact Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, 1601 Lind Avenue
SW., Renton, WA 98057-3356; phone: 425-917-6440; fax: 425-917-6432;
email: nancy.marsh@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(t) 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
October 3, 2012 (77 FR 52212, August 29, 2012).
(i) Boeing Special Attention Service Bulletin 757-53-0094,
Revision 1, dated August 12, 2009.
(ii) Reserved.
(4) The following service information was approved for IBR on
May 24, 2004 (69 FR 25481, May 7, 2004).
(i) Boeing Special Attention Service Bulletin 757-53-0089, dated
March 18, 2004.
(ii) Reserved.
(5) 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; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(6) You may review copies of the 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.
(7) You may also review copies of the service information that
is incorporated by
[[Page 75831]]
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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 5, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-30305 Filed 12-21-12; 8:45 am]
BILLING CODE 4910-13-P
