Airworthiness Directives; the Boeing Company Airplanes, 58722-58726 [2011-24356]
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58722
Proposed Rules
Federal Register
Vol. 76, No. 184
Thursday, September 22, 2011
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0991; Directorate
Identifier 2010–NM–134–AD]
RIN 2120–AA64
Airworthiness Directives; the Boeing
Company Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Model 747–100, 747–100B, 747–200B,
747–200C, 747–200F, 747–400F, 747SR,
and 747SP series airplanes, without a
stretched upper deck or stretched upper
deck modification. The existing AD
currently requires repetitive inspections
for cracks of each affected tension tie
and of the surrounding structure, and
related investigative and corrective
actions if necessary. This proposed AD
would also require, for certain airplanes,
modifying the tension tie structure or
tension tie and frame structure at certain
stations; and a post-modification
inspection of the modified area and
post-modification repetitive inspections
of the unmodified area, and repair if
necessary. Doing the modification
would terminate the repetitive
inspection requirements in the existing
AD. This proposed AD would reduce
the compliance time and add
inspections for certain airplanes. This
proposed AD results from reports that
certain airplanes have tension ties that
are susceptible to widespread fatigue
damage. This proposed AD also results
from reports of cracks on the forward
and aft tension tie channels at station
(STA) 740 and STA 760, and a
determination that initial inspection
intervals need to be reduced. We are
proposing this AD to prevent tension
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SUMMARY:
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ties from becoming severed or
disconnected from the frames, which
could lead to rapid in-flight
decompression.
DATES: We must receive comments on
this proposed AD by November 7, 2011.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://www.regulations.
gov; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Steven Fox, Senior Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; phone: (425)
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917–6425; fax: (425) 917–6590; e-mail:
steven.fox@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2011–0991; Directorate Identifier
2010–NM–134–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://www.
regulations.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On December 30, 2005, we issued AD
2006–01–07, Amendment 39–14446 (71
FR 1947, January 12, 2006), for certain
Model 747–100, 747–100B, 747–200B,
747–200C, 747–200F, 747–400F, 747SR,
and 747SP series airplanes. That AD
requires detailed and high-frequency
eddy current (HFEC) inspections for
cracks of each affected tension tie and
of the surrounding structure, and related
investigative and corrective actions if
necessary. That AD resulted from a
report of a crack in the tension tie at the
body station (BS) 820 frame connection,
and cracks found on the Boeing 747SR
fatigue-test airplane in both the tension
ties and frames at the tension tie to
frame connections at BS 800, 820, and
840. We issued that AD to find and fix
cracks in the tension ties, which could
lead to cracks in the skin and body
frame and result in rapid in-flight
depressurization of the airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2006–01–07,
Amendment 39 14446 (71 FR 1947,
January 12, 2006), specifies that we
consider the requirements to be
‘‘interim action’’ and that the
manufacturer was developing a
modification to address the unsafe
condition. That AD explains that we
might consider further rulemaking if a
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modification is developed, approved,
and available. The manufacturer now
has developed such a modification, and
we have determined that further
rulemaking is indeed necessary; this
proposed AD follows from that
determination.
This proposed AD also results from
reports of cracks on the forward and aft
tension tie channels at station (STA) 740
and STA 760 on a Model 747–400F
airplane, and a determination that
initial inspection compliance times
need to be reduced.
Relevant Service Information
AD 2006–01–07, Amendment 39–
14446 (71 FR 1947, January 12, 2006),
refers to Boeing Special Attention
Service Bulletin 747–53–2502, dated
April 21, 2005, as the appropriate
source of service information for doing
the required actions. We have reviewed
Boeing Alert Service Bulletin 747–
53A2502, Revision 1, dated June 17,
2010. For Group 2 airplanes, Boeing
Alert Service Bulletin 747–53A2502,
Revision 1, dated June 17, 2010, reduces
the compliance time for the detailed and
HFEC inspections of the tension ties;
adds a one-time general visual
inspection of the tension ties for correct
configuration; adds a detailed and open
fastener-hole HFEC inspection for
cracks in the tension tie and frame if an
incorrect configuration is found; and
adds repair of the cracked tension tie, or
instructions to contact Boeing for repair
instructions.
We have also reviewed Boeing Alert
Service Bulletin 747–53A2605, Revision
1, dated May 27, 2010, which is not
applicable to Model 747SP airplanes.
Boeing Alert Service Bulletin 747–
53A2605, Revision 1, dated May 27,
2010, describes procedures for
modification of the left- and right-side
tension tie structure or tension tie and
frame structure at certain body stations,
repetitive inspections of the modified
area, repetitive detailed inspections for
cracks on the unmodified area of the
tension tie, and repair if necessary.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to develop on
other airplanes of the same type design.
For this reason, we are proposing this
AD, which would supersede AD 2006–
01–07, Amendment 39–14446 (71 FR
1947, January 12, 2006), and would
retain the requirements of the existing
AD with a reduced compliance time for
certain airplanes. This proposed AD
would also require accomplishing the
actions specified in Boeing Alert Service
Bulletin 747–53A2502, Revision 1,
dated June 17, 2010; and Boeing Alert
Service Bulletin 747–53A2605, Revision
1, dated May 27, 2010; as described
previously. Doing the modification
specified in this proposed AD ends the
existing repetitive inspections in the
existing AD.
No Repetitive Intervals for PostModification Inspections of the
Modified Areas
Boeing Alert Service Bulletin 747–
53A2605, Revision 1, dated May 27,
2010, specifies to contact Boeing for the
intervals for the repetitive postmodification inspections of the
modified areas, nor does this proposed
AD include those intervals. Postmodification inspection guidance for
paragraph (j)(2) of this proposed AD
may be defined in an approved
alternative method of compliance
(AMOC).
Changes to Existing AD
In this NPRM, we have identified the
legal name of the manufacturer as
published in the most recent type
certificate data sheet for the affected
airplane models.
Boeing Commercial Airplanes has
received an Organization Designation
Authorization (ODA), which replaces
the previous designation as a Delegation
Option Authorization (DOA) holder. We
have revised paragraph (n) of this
proposed AD to add delegation of
authority to Boeing Commercial
Airplanes ODA to approve an
alternative method of compliance for
certain repairs required by this AD.
We have added a new paragraph (d)
to this NPRM to provide the Air
Transport Association (ATA) of America
subject code 53: Fuselage. This code is
added to make this proposed AD
parallel with other new AD actions. We
have re-identified subsequent
paragraphs accordingly.
Differences Between the Proposed AD
and the Service Information
The service bulletins specify to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions in
one of the following ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes ODA whom we
have authorized to make those findings.
Boeing Alert Service Bulletin 747–
53A2605, Revision 1, dated May 27,
2010, includes a modification for all
airplanes except for Model 747SP
airplanes. This proposed AD requires
that modification for Model 747SP
airplanes.
Costs of Compliance
There are about 276 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Average
labor rate
per hour
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Action
Work hours
Inspection (required
by AD 2006–01–07,
Amendment 39–
14446 (71 FR 1947,
January 12, 2006)).
8 per tension tie location, between 8 and
12 tension tie locations per airplane,
depending on airplane configuration.
6 ................................
Between 30 and 85,
depending on airplane configuration.
One-time inspection
(new proposed action for Group 2 airplanes).
Modification (new proposed action).
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Number
of U.S.registered
airplanes
Parts
Cost per airplane
$85
$0 ..............................
Between $5,440 and
$8,160 per inspection cycle.
141
85
None .........................
510 ............................
86
$43,860.
85
Between $18,657 and
$635,004.
Between $21,207 and
642,229.
86
Between $1,823,802
and $55,231,694.
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Fleet cost
Between $767,040
and $1,150,560 per
inspection cycle.
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ESTIMATED COSTS—Continued
Average
labor rate
per hour
Action
Work hours
Inspection for unmodified area.
2 per tension tie location, between 8 and
12 tension tie locations per airplane,
depending on airplane configuration.
2 per tension tie location, between 8 and
12 tension tie locations per airplane,
depending on airplane configuration.
Inspection for modified
area.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979); and
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
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Number
of U.S.registered
airplanes
Parts
Cost per airplane
85
None .........................
Between $1,360 and
$2,040.
86
Between $116,960
and $175,440.
85
None .........................
Between $1,360 and
$2,040.
86
Between $116,960
and $175,440.
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14446 (71 FR
1947, January 12, 2006) and adding the
following new AD:
The Boeing Company: Docket No. FAA–
2011–0991; Directorate Identifier 2010–
NM–134–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by November 7, 2011.
Affected ADs
(b) This AD supersedes AD 2006–01–07,
Amendment 39–14446 (71 FR 1947, January
12, 2006).
Applicability
(c) This AD applies to The Boeing
Company Model 747–100, 747–100B, 747–
200B, 747–200C, 747–200F, 747–400F,
747SR, and 747SP series airplanes,
certificated in any category, as identified in
Boeing Alert Service Bulletin 747–53A2502,
Revision 1, dated June 17, 2010.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
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Unsafe Condition
(e) This proposed AD results from reports
that certain airplanes have tension ties that
are susceptible to widespread fatigue
damage. This proposed AD also results from
reports of cracks on the forward and aft
tension tie channels at station (STA) 740 and
STA 760, and a determination that initial
inspection compliance times need to be
reduced. The Federal Aviation
Administration is issuing this AD to prevent
tension ties from becoming severed or
disconnected from the frames, which could
lead to rapid in-flight decompression.
Compliance
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
Fleet cost
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006–
01–07, Amendment 39–14446 (71 FR 1947,
January 12, 2006), With Reduced
Compliance Time for Certain Airplanes
Repetitive Inspections and Corrective
Actions
(g) For Group 1, and Groups 3 through 6
airplanes identified in Boeing Special
Attention Service Bulletin 747–53–2502,
dated April 21, 2005; at the applicable time
in paragraph (g)(1) or (g)(2) of this AD: Do
detailed and high-frequency eddy current
inspections for cracking of each affected
tension tie and of the surrounding structure.
If any cracking is found: Before further flight,
do all applicable corrective and related
investigative actions. Do all actions in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–53–2502, dated April
21, 2005; or Boeing Alert Service Bulletin
747–53A2502, Revision 1, dated June 17,
2010. Where Boeing Special Attention
Service Bulletin 747–53–2502, dated April
21, 2005; or Boeing Alert Service Bulletin
747–53A2502, Revision 1, dated June 17,
2010; specifies to contact Boeing for repair
instructions: Before further flight, repair the
area using a method approved in accordance
with paragraph (n) of this AD. As of the
effective date of this AD, only Boeing Alert
Service Bulletin 747–53A2502, Revision 1,
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dated June 17, 2010, may be used for the
actions required in this paragraph.
(1) For airplanes identified in Boeing
Special Attention Service Bulletin 747–53–
2502, dated April 21, 2005, as Groups 1, 3,
and 6 airplanes: Do the first inspections
before the accumulation of 20,000 total flight
cycles, or within 1,000 flight cycles after
February 16, 2006 (the effective date of AD
2006–01–07, Amendment 39–14446 (71 FR
1947, January 12, 2006)), whichever occurs
later; and repeat the inspections thereafter at
intervals not to exceed 4,000 flight cycles
until the modification required by paragraph
(j) of this AD is accomplished.
(2) For airplanes identified in Boeing
Special Attention Service Bulletin 747–53–
2502, dated April 21, 2005, as Group 4 and
5 airplanes: Do the first inspections before
the accumulation of 17,000 total flight cycles,
or within 1,000 flight cycles after February
16, 2006, whichever occurs later; and repeat
the inspections thereafter at intervals not to
exceed 3,000 flight cycles until the
modification required by paragraph (j) of this
AD is accomplished.
Inspection for Group 2 Airplanes With
Reduced Compliance Times
(h) For Group 2 airplanes identified in
Boeing Alert Service Bulletin 747–53A2502,
Revision 1, dated June 17, 2010: At the
applicable times specified in paragraphs
(h)(1) and (h)(2) of this AD, do detailed and
high-frequency eddy current inspections for
cracking of each affected tension tie and of
the surrounding structure, in accordance
with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
747–53–2502, dated April 21, 2005; or
Boeing Alert Service Bulletin 747–53A2502,
Revision 1, dated June 17, 2010. If any
cracking is found: Before further flight, do all
applicable corrective and related
investigative actions. Do all actions in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–53–2502, dated April
21, 2005; or Boeing Alert Service Bulletin
747–53A2502, Revision 1, dated June 17,
2010. Where Boeing Special Attention
Service Bulletin 747–53–2502, dated April
21, 2005; or Boeing Alert Service Bulletin
747–53A2502, Revision 1, dated June 17,
2010; specify to contact Boeing for repair
instructions: Before further flight, repair the
area using a method approved in accordance
with paragraph (n) of this AD. As of the
effective date of this AD, only Boeing Alert
Service Bulletin 747–53A2502, Revision 1,
dated June 17, 2010, may be used. Repeat the
inspections thereafter at intervals not to
exceed 3,000 flight cycles until the
modification required by paragraph (j) of this
AD is accomplished.
(1) For STA 780 through 940: Before the
accumulation of 17,000 total flight cycles, or
within 1,000 flight cycles after February 16,
2006, whichever occurs later.
(2) For STA 720, 740, and 760: At the
earlier of the times of paragraph (h)(2)(i) or
(h)(2)(ii).
(i) Before the accumulation of 17,000 total
flight cycles, or within 1,000 flight cycles
after February 16, 2006, whichever occurs
later.
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(ii) Before the accumulation of 8,000 total
flight cycles, or within 1,000 flight cycles
after the effective date of this AD, whichever
occurs later.
New Requirements of This AD
One-Time Inspection for Group 2 Airplanes
(i) For airplanes identified in Boeing Alert
Service Bulletin 747–53A2502, Revision 1,
dated June 17, 2010, as Group 2 airplanes:
Before the accumulation of 8,000 total flight
cycles, or within 1,000 flight cycles after the
effective date of this AD, whichever occurs
later: Do a general visual inspection for
correct configuration, as identified in Boeing
Alert Service Bulletin 747–53A2502,
Revision 1, dated June 17, 2010, of each
affected tension tie and of the surrounding
structure, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2502, Revision 1,
dated June 17, 2010.
(1) If all tension ties match the correct
configurations specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2502, Revision 1,
dated June 17, 2010, no further work is
required by this paragraph.
(2) If any incorrect configuration is found,
before further flight, do detailed and open
fastener-hole HFEC inspections for cracks in
the tension tie and frame, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–53A2502,
Revision 1, dated June 17, 2010.
(i) If no crack is found during the
inspection required by paragraph (i)(2) of this
AD, before further flight, install the correct
configuration for the tension ties at locations
where the incorrect configuration was found,
using a method approved in accordance with
the procedures specified in paragraph (n) of
this AD.
(ii) If any crack is found during the
inspection required by paragraph (i)(2) of this
AD, before further flight, do the actions in
paragraphs (i)(2)(ii)(A) and (i)(2)(ii)(B) of this
AD.
(A) Repair the crack in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2502, Revision 1,
dated June 17, 2010, except where Boeing
Alert Service Bulletin 747–53A2502,
Revision 1, dated June 17, 2010, specifies to
contact Boeing for appropriate action: Before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (n) of this AD.
(B) Install the correct configuration for the
tension ties at locations where the incorrect
configuration was found, using a method
approved in accordance with the procedures
specified in paragraph (n) of this AD.
Modification
(j) Before the accumulation of 30,000 total
flight cycles, or within 3,000 flight cycles
after the effective date of this AD, whichever
occurs later, modify the left- and right-side
tension tie structure or left- and right-side
tension tie and frame structure, at specified
stations, in accordance with the applicable
method specified in paragraph (j)(1) or (j)(2)
of this AD. Accomplishment of the
modification in this paragraph terminates the
repetitive inspection requirements in
paragraphs (g)(1), (g)(2), and (h) of this AD.
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(1) For airplanes identified in Boeing Alert
Service Bulletin 747–53A2605, Revision 1,
dated May 27, 2010: Do the modification, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2605, Revision 1, dated May 27,
2010.
(2) For airplanes not identified in Boeing
Alert Service Bulletin 747–53A2605,
Revision 1, dated May 27, 2010: Do the
modification, using a method approved in
accordance with paragraph (n) of this AD.
Note 1: For airplanes identified in
paragraph (j)(2) of this AD, post-modification
inspection guidance may be defined in an
approved alternative method of compliance
(AMOC) for paragraph (j)(2) of this AD.
Post-Modification Inspection of the Modified
Areas
(k) For airplanes identified in paragraph
(j)(1) of this AD, within 20,000 flight cycles
after doing the modification required by
paragraph (j) of this AD, do an inspection for
cracks of the modified areas of the left- and
right-side tension tie structure and frame
structure, in accordance with a method
approved with the procedures specified in
paragraph (n) of this AD. 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 (n) of this AD.
Post-Modification Repetitive Inspections of
the Unmodified Areas
(l) For airplanes identified in paragraph
(j)(1) of this AD, within 6,000 flight cycles
after doing the modification required by
paragraph (j) of this AD, do a detailed
inspection for cracks on the unmodified areas
of the left- and right-side tension tie structure
and frame structure, at certain stations, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2605, Revision 1, dated May 27,
2010. If any crack is found during any
inspection required by this paragraph, before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (n) of this AD. Repeat
the inspection of the unmodified areas
thereafter at intervals not to exceed 6,000
flight cycles.
Note 2: Boeing Alert Service Bulletin 747–
53A2605, Revision 1, dated May 27, 2010,
refers to Section 51–10–02 of the Boeing 747–
400F Structural Repair Manual (SRM) and
Section 51–10–01 of the Boeing 747–100/
200/300 SRM as additional sources of
guidance for removing small cracks and
fatigue damage material from the existing
holes in the unmodified center section of the
tension tie channels. Where those SRM
sections state that ‘‘zero-timing must only be
used where specifically permitted in an SRM
chapter-section-repair,’’ this AD allows the
zero-timing procedures specified in those
SRM sections.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(m) Actions done in accordance with
Boeing Alert Service Bulletin 747–53A2605,
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emcdonald on DSK5VPTVN1PROD with PROPOSALS
dated October 8, 2009, before the effective
date of this AD are acceptable for compliance
with the corresponding actions required by
paragraphs (j), (k), and (l) of this AD.
Alternative Methods of Compliance
(AMOCs)
(n)(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 e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
to make those findings. For a repair method
to be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Certain actions required by paragraph
(g) of this AD are approved as AMOCs for the
requirements specified in paragraphs
(n)(4)(i), (n)(4)(ii), and (n)(4)(iii) of this AD.
All provisions of the referenced ADs in
paragraphs (n)(4)(i), (n)(4)(ii), and (n)(4)(iii)
of this AD, including applicable postmodification inspection thresholds, remain
fully applicable and must be complied with.
(i) Repairs or modifications of the aft
tension tie channels done in accordance with
this AD are AMOCs for the repair
requirements of paragraph A. of AD 84–19–
01, Amendment 39–4913 (49 FR 35365,
September 17, 1984), and paragraphs (a)(2)
and (b)(2) of AD 94–13–06, Amendment 39–
8946 (59 FR 32879, June 27, 1994).
(ii) The inspection requirements of this AD
are AMOCs for the post-modification
inspection requirements of paragraph B. of
AD 84–19–01, Amendment 39–4913 (49 FR
35365, September 17, 1984), and paragraph
(b) of AD 94–13–06, Amendment 39–8946
(59 FR 32879, June 27, 1994).
(iii) The inspection requirements of this
AD are AMOCs for the inspections of
Structural Significant Item (SSI) F–19A of
Boeing Supplemental Structural Inspection
Document D6–35022, Revision G, dated
December 2000, as required by paragraphs (h)
and (i) of AD 2004–07–22 R1, Amendment
39–15326 (73 FR 1052, January 7, 2008),
corrected on February 14, 2008 (73 FR 8589).
Related Information
(o) For more information about this AD,
contact Steven Fox, Senior Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle ACO, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6425; fax (425) 917–6590; e-mail:
steven.fox@faa.gov.
VerDate Mar<15>2010
18:25 Sep 21, 2011
Jkt 223001
(p) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You
may review copies of the referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on
September 14, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–24356 Filed 9–21–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2011–0591; Airspace
Docket No. 11–ASO–26]
Proposed Amendment of Class E
Airspace; Springfield, TN
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
amend Class E Airspace in the
Springfield, TN area. Aydelotte Airport
has been abandoned and controlled
airspace is no longer needed. Airspace
reconfiguration is necessary for the
continued safety and management of
instrument flight rules (IFR) operations
within the Springfield, TN airspace
area.
SUMMARY:
0901 UTC. Comments must be
received on or before November 7, 2011.
ADDRESSES: Send comments on this rule
to: U.S. Department of Transportation,
Docket Operations, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590–0001; Telephone: 1–800–
647–5527; Fax: 202–493–2251. You
must identify the Docket Number FAA–
2011–0591; Airspace Docket No. 11–
ASO–26, at the beginning of your
comments. You may also submit and
review received comments through the
Internet at
https://www.regulations.gov.
FOR FURTHER INFORMATION CONTACT: John
Fornito, Operations Support Group,
Eastern Service Center, Federal Aviation
Administration, P.O. Box 20636,
DATES:
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
Atlanta, Georgia 30320; telephone (404)
305–6364.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to
comment on this rule by submitting
such written data, views, or arguments,
as they may desire. Comments that
provide the factual basis supporting the
views and suggestions presented are
particularly helpful in developing
reasoned regulatory decisions on the
proposal. Comments are specifically
invited on the overall regulatory,
aeronautical, economic, environmental,
and energy-related aspects of the
proposal.
Communications should identify both
docket numbers (FAA Docket No. FAA–
2011–0591; Airspace Docket No. 11–
ASO–26) and be submitted in triplicate
to the Docket Management System (see
ADDRESSES section for address and
phone number). You may also submit
comments through the Internet at https://
www.regulations.gov.
Annotators wishing the FAA to
acknowledge receipt of their comments
on this action must submit with those
comments a self-addressed stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. FAA–2011–0591; Airspace
Docket No. 11–ASO–26.’’ The postcard
will be date/time stamped and returned
to the commenter.
All communications received before
the specified closing date for comments
will be considered before taking action
on the proposed rule. The proposal
contained in this notice may be changed
in light of the comments received. A
report summarizing each substantive
public contact with FAA personnel
concerned with this rulemaking will be
filed in the docket.
Availability of NPRMs
An electronic copy of this document
may be downloaded from and
comments submitted through https://
www.regulations.gov. Recently
published rulemaking documents can
also be accessed through the FAA’s Web
page at https://www.faa.gov/airports_
airtraffic/air_traffic/publications/
airspace_amendments/.
You may review the public docket
containing the proposal, any comments
received and any final disposition in
person in the Dockets Office (see the
ADDRESSES section for address and
phone number) between 9 a.m. and
5 p.m., Monday through Friday, except
Federal Holidays. An informal docket
may also be examined during normal
business hours at the office of the
Eastern Service Center, Federal Aviation
E:\FR\FM\22SEP1.SGM
22SEP1
]]>Agencies
[Federal Register Volume 76, Number 184 (Thursday, September 22, 2011)]
[Proposed Rules]
[Pages 58722-58726]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-24356]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 76, No. 184 / Thursday, September 22, 2011 /
Proposed Rules
[[Page 58722]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0991; Directorate Identifier 2010-NM-134-AD]
RIN 2120-AA64
Airworthiness Directives; the Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Model 747-100, 747-100B, 747-
200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP series airplanes,
without a stretched upper deck or stretched upper deck modification.
The existing AD currently requires repetitive inspections for cracks of
each affected tension tie and of the surrounding structure, and related
investigative and corrective actions if necessary. This proposed AD
would also require, for certain airplanes, modifying the tension tie
structure or tension tie and frame structure at certain stations; and a
post-modification inspection of the modified area and post-modification
repetitive inspections of the unmodified area, and repair if necessary.
Doing the modification would terminate the repetitive inspection
requirements in the existing AD. This proposed AD would reduce the
compliance time and add inspections for certain airplanes. This
proposed AD results from reports that certain airplanes have tension
ties that are susceptible to widespread fatigue damage. This proposed
AD also results from reports of cracks on the forward and aft tension
tie channels at station (STA) 740 and STA 760, and a determination that
initial inspection intervals need to be reduced. We are proposing this
AD to prevent tension ties from becoming severed or disconnected from
the frames, which could lead to rapid in-flight decompression.
DATES: We must receive comments on this proposed AD by November 7,
2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Steven Fox, Senior Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone:
(425) 917-6425; fax: (425) 917-6590; e-mail: steven.fox@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0991;
Directorate Identifier 2010-NM-134-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On December 30, 2005, we issued AD 2006-01-07, Amendment 39-14446
(71 FR 1947, January 12, 2006), for certain Model 747-100, 747-100B,
747-200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP series
airplanes. That AD requires detailed and high-frequency eddy current
(HFEC) inspections for cracks of each affected tension tie and of the
surrounding structure, and related investigative and corrective actions
if necessary. That AD resulted from a report of a crack in the tension
tie at the body station (BS) 820 frame connection, and cracks found on
the Boeing 747SR fatigue-test airplane in both the tension ties and
frames at the tension tie to frame connections at BS 800, 820, and 840.
We issued that AD to find and fix cracks in the tension ties, which
could lead to cracks in the skin and body frame and result in rapid in-
flight depressurization of the airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2006-01-07, Amendment 39 14446 (71 FR 1947,
January 12, 2006), specifies that we consider the requirements to be
``interim action'' and that the manufacturer was developing a
modification to address the unsafe condition. That AD explains that we
might consider further rulemaking if a
[[Page 58723]]
modification is developed, approved, and available. The manufacturer
now has developed such a modification, and we have determined that
further rulemaking is indeed necessary; this proposed AD follows from
that determination.
This proposed AD also results from reports of cracks on the forward
and aft tension tie channels at station (STA) 740 and STA 760 on a
Model 747-400F airplane, and a determination that initial inspection
compliance times need to be reduced.
Relevant Service Information
AD 2006-01-07, Amendment 39-14446 (71 FR 1947, January 12, 2006),
refers to Boeing Special Attention Service Bulletin 747-53-2502, dated
April 21, 2005, as the appropriate source of service information for
doing the required actions. We have reviewed Boeing Alert Service
Bulletin 747-53A2502, Revision 1, dated June 17, 2010. For Group 2
airplanes, Boeing Alert Service Bulletin 747-53A2502, Revision 1, dated
June 17, 2010, reduces the compliance time for the detailed and HFEC
inspections of the tension ties; adds a one-time general visual
inspection of the tension ties for correct configuration; adds a
detailed and open fastener-hole HFEC inspection for cracks in the
tension tie and frame if an incorrect configuration is found; and adds
repair of the cracked tension tie, or instructions to contact Boeing
for repair instructions.
We have also reviewed Boeing Alert Service Bulletin 747-53A2605,
Revision 1, dated May 27, 2010, which is not applicable to Model 747SP
airplanes. Boeing Alert Service Bulletin 747-53A2605, Revision 1, dated
May 27, 2010, describes procedures for modification of the left- and
right-side tension tie structure or tension tie and frame structure at
certain body stations, repetitive inspections of the modified area,
repetitive detailed inspections for cracks on the unmodified area of
the tension tie, and repair if necessary.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2006-01-07, Amendment 39-14446 (71 FR 1947, January
12, 2006), and would retain the requirements of the existing AD with a
reduced compliance time for certain airplanes. This proposed AD would
also require accomplishing the actions specified in Boeing Alert
Service Bulletin 747-53A2502, Revision 1, dated June 17, 2010; and
Boeing Alert Service Bulletin 747-53A2605, Revision 1, dated May 27,
2010; as described previously. Doing the modification specified in this
proposed AD ends the existing repetitive inspections in the existing
AD.
No Repetitive Intervals for Post-Modification Inspections of the
Modified Areas
Boeing Alert Service Bulletin 747-53A2605, Revision 1, dated May
27, 2010, specifies to contact Boeing for the intervals for the
repetitive post-modification inspections of the modified areas, nor
does this proposed AD include those intervals. Post-modification
inspection guidance for paragraph (j)(2) of this proposed AD may be
defined in an approved alternative method of compliance (AMOC).
Changes to Existing AD
In this NPRM, we have identified the legal name of the manufacturer
as published in the most recent type certificate data sheet for the
affected airplane models.
Boeing Commercial Airplanes has received an Organization
Designation Authorization (ODA), which replaces the previous
designation as a Delegation Option Authorization (DOA) holder. We have
revised paragraph (n) of this proposed AD to add delegation of
authority to Boeing Commercial Airplanes ODA to approve an alternative
method of compliance for certain repairs required by this AD.
We have added a new paragraph (d) to this NPRM to provide the Air
Transport Association (ATA) of America subject code 53: Fuselage. This
code is added to make this proposed AD parallel with other new AD
actions. We have re-identified subsequent paragraphs accordingly.
Differences Between the Proposed AD and the Service Information
The service bulletins specify to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes ODA whom we have authorized to make those findings.
Boeing Alert Service Bulletin 747-53A2605, Revision 1, dated May
27, 2010, includes a modification for all airplanes except for Model
747SP airplanes. This proposed AD requires that modification for Model
747SP airplanes.
Costs of Compliance
There are about 276 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average Number of
labor U.S.-
Action Work hours rate per Parts Cost per airplane registered Fleet cost
hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (required by AD 2006-01- 8 per tension tie $85 $0.................... Between $5,440 and 141 Between $767,040 and
07, Amendment 39-14446 (71 FR location, between 8 $8,160 per $1,150,560 per
1947, January 12, 2006)). and 12 tension tie inspection cycle. inspection cycle.
locations per
airplane, depending
on airplane
configuration.
One-time inspection (new proposed 6..................... 85 None.................. 510.................. 86 $43,860.
action for Group 2 airplanes).
Modification (new proposed action). Between 30 and 85, 85 Between $18,657 and Between $21,207 and 86 Between $1,823,802
depending on airplane $635,004. 642,229. and $55,231,694.
configuration.
[[Page 58724]]
Inspection for unmodified area..... 2 per tension tie 85 None.................. Between $1,360 and 86 Between $116,960 and
location, between 8 $2,040. $175,440.
and 12 tension tie
locations per
airplane, depending
on airplane
configuration.
Inspection for modified area....... 2 per tension tie 85 None.................. Between $1,360 and 86 Between $116,960 and
location, between 8 $2,040. $175,440.
and 12 tension tie
locations per
airplane, depending
on airplane
configuration.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Amendment 39-14446 (71 FR
1947, January 12, 2006) and adding the following new AD:
The Boeing Company: Docket No. FAA-2011-0991; Directorate Identifier
2010-NM-134-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by November
7, 2011.
Affected ADs
(b) This AD supersedes AD 2006-01-07, Amendment 39-14446 (71 FR
1947, January 12, 2006).
Applicability
(c) This AD applies to The Boeing Company Model 747-100, 747-
100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP
series airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin 747-53A2502, Revision 1, dated June
17, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This proposed AD results from reports that certain airplanes
have tension ties that are susceptible to widespread fatigue damage.
This proposed AD also results from reports of cracks on the forward
and aft tension tie channels at station (STA) 740 and STA 760, and a
determination that initial inspection compliance times need to be
reduced. The Federal Aviation Administration is issuing this AD to
prevent tension ties from becoming severed or disconnected from the
frames, which could lead to rapid in-flight decompression.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006-01-07, Amendment 39-14446 (71 FR
1947, January 12, 2006), With Reduced Compliance Time for Certain
Airplanes
Repetitive Inspections and Corrective Actions
(g) For Group 1, and Groups 3 through 6 airplanes identified in
Boeing Special Attention Service Bulletin 747-53-2502, dated April
21, 2005; at the applicable time in paragraph (g)(1) or (g)(2) of
this AD: Do detailed and high-frequency eddy current inspections for
cracking of each affected tension tie and of the surrounding
structure. If any cracking is found: Before further flight, do all
applicable corrective and related investigative actions. Do all
actions in accordance with the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747-53-2502, dated April 21,
2005; or Boeing Alert Service Bulletin 747-53A2502, Revision 1,
dated June 17, 2010. Where Boeing Special Attention Service Bulletin
747-53-2502, dated April 21, 2005; or Boeing Alert Service Bulletin
747-53A2502, Revision 1, dated June 17, 2010; specifies to contact
Boeing for repair instructions: Before further flight, repair the
area using a method approved in accordance with paragraph (n) of
this AD. As of the effective date of this AD, only Boeing Alert
Service Bulletin 747-53A2502, Revision 1,
[[Page 58725]]
dated June 17, 2010, may be used for the actions required in this
paragraph.
(1) For airplanes identified in Boeing Special Attention Service
Bulletin 747-53-2502, dated April 21, 2005, as Groups 1, 3, and 6
airplanes: Do the first inspections before the accumulation of
20,000 total flight cycles, or within 1,000 flight cycles after
February 16, 2006 (the effective date of AD 2006-01-07, Amendment
39-14446 (71 FR 1947, January 12, 2006)), whichever occurs later;
and repeat the inspections thereafter at intervals not to exceed
4,000 flight cycles until the modification required by paragraph (j)
of this AD is accomplished.
(2) For airplanes identified in Boeing Special Attention Service
Bulletin 747-53-2502, dated April 21, 2005, as Group 4 and 5
airplanes: Do the first inspections before the accumulation of
17,000 total flight cycles, or within 1,000 flight cycles after
February 16, 2006, whichever occurs later; and repeat the
inspections thereafter at intervals not to exceed 3,000 flight
cycles until the modification required by paragraph (j) of this AD
is accomplished.
Inspection for Group 2 Airplanes With Reduced Compliance Times
(h) For Group 2 airplanes identified in Boeing Alert Service
Bulletin 747-53A2502, Revision 1, dated June 17, 2010: At the
applicable times specified in paragraphs (h)(1) and (h)(2) of this
AD, do detailed and high-frequency eddy current inspections for
cracking of each affected tension tie and of the surrounding
structure, in accordance with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 747-53-2502, dated April
21, 2005; or Boeing Alert Service Bulletin 747-53A2502, Revision 1,
dated June 17, 2010. If any cracking is found: Before further
flight, do all applicable corrective and related investigative
actions. Do all actions in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-53-
2502, dated April 21, 2005; or Boeing Alert Service Bulletin 747-
53A2502, Revision 1, dated June 17, 2010. Where Boeing Special
Attention Service Bulletin 747-53-2502, dated April 21, 2005; or
Boeing Alert Service Bulletin 747-53A2502, Revision 1, dated June
17, 2010; specify to contact Boeing for repair instructions: Before
further flight, repair the area using a method approved in
accordance with paragraph (n) of this AD. As of the effective date
of this AD, only Boeing Alert Service Bulletin 747-53A2502, Revision
1, dated June 17, 2010, may be used. Repeat the inspections
thereafter at intervals not to exceed 3,000 flight cycles until the
modification required by paragraph (j) of this AD is accomplished.
(1) For STA 780 through 940: Before the accumulation of 17,000
total flight cycles, or within 1,000 flight cycles after February
16, 2006, whichever occurs later.
(2) For STA 720, 740, and 760: At the earlier of the times of
paragraph (h)(2)(i) or (h)(2)(ii).
(i) Before the accumulation of 17,000 total flight cycles, or
within 1,000 flight cycles after February 16, 2006, whichever occurs
later.
(ii) Before the accumulation of 8,000 total flight cycles, or
within 1,000 flight cycles after the effective date of this AD,
whichever occurs later.
New Requirements of This AD
One-Time Inspection for Group 2 Airplanes
(i) For airplanes identified in Boeing Alert Service Bulletin
747-53A2502, Revision 1, dated June 17, 2010, as Group 2 airplanes:
Before the accumulation of 8,000 total flight cycles, or within
1,000 flight cycles after the effective date of this AD, whichever
occurs later: Do a general visual inspection for correct
configuration, as identified in Boeing Alert Service Bulletin 747-
53A2502, Revision 1, dated June 17, 2010, of each affected tension
tie and of the surrounding structure, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2502, Revision 1, dated June 17, 2010.
(1) If all tension ties match the correct configurations
specified in the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2502, Revision 1, dated June 17, 2010, no further
work is required by this paragraph.
(2) If any incorrect configuration is found, before further
flight, do detailed and open fastener-hole HFEC inspections for
cracks in the tension tie and frame, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2502, Revision 1, dated June 17, 2010.
(i) If no crack is found during the inspection required by
paragraph (i)(2) of this AD, before further flight, install the
correct configuration for the tension ties at locations where the
incorrect configuration was found, using a method approved in
accordance with the procedures specified in paragraph (n) of this
AD.
(ii) If any crack is found during the inspection required by
paragraph (i)(2) of this AD, before further flight, do the actions
in paragraphs (i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD.
(A) Repair the crack in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2502, Revision
1, dated June 17, 2010, except where Boeing Alert Service Bulletin
747-53A2502, Revision 1, dated June 17, 2010, specifies to contact
Boeing for appropriate action: Before further flight, repair the
crack using a method approved in accordance with the procedures
specified in paragraph (n) of this AD.
(B) Install the correct configuration for the tension ties at
locations where the incorrect configuration was found, using a
method approved in accordance with the procedures specified in
paragraph (n) of this AD.
Modification
(j) Before the accumulation of 30,000 total flight cycles, or
within 3,000 flight cycles after the effective date of this AD,
whichever occurs later, modify the left- and right-side tension tie
structure or left- and right-side tension tie and frame structure,
at specified stations, in accordance with the applicable method
specified in paragraph (j)(1) or (j)(2) of this AD. Accomplishment
of the modification in this paragraph terminates the repetitive
inspection requirements in paragraphs (g)(1), (g)(2), and (h) of
this AD.
(1) For airplanes identified in Boeing Alert Service Bulletin
747-53A2605, Revision 1, dated May 27, 2010: Do the modification, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2605, Revision 1, dated May 27, 2010.
(2) For airplanes not identified in Boeing Alert Service
Bulletin 747-53A2605, Revision 1, dated May 27, 2010: Do the
modification, using a method approved in accordance with paragraph
(n) of this AD.
Note 1: For airplanes identified in paragraph (j)(2) of this AD,
post-modification inspection guidance may be defined in an approved
alternative method of compliance (AMOC) for paragraph (j)(2) of this
AD.
Post-Modification Inspection of the Modified Areas
(k) For airplanes identified in paragraph (j)(1) of this AD,
within 20,000 flight cycles after doing the modification required by
paragraph (j) of this AD, do an inspection for cracks of the
modified areas of the left- and right-side tension tie structure and
frame structure, in accordance with a method approved with the
procedures specified in paragraph (n) of this AD. 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 (n) of this
AD.
Post-Modification Repetitive Inspections of the Unmodified Areas
(l) For airplanes identified in paragraph (j)(1) of this AD,
within 6,000 flight cycles after doing the modification required by
paragraph (j) of this AD, do a detailed inspection for cracks on the
unmodified areas of the left- and right-side tension tie structure
and frame structure, at certain stations, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2605, Revision 1, dated May 27, 2010. If any crack is found
during any inspection required by this paragraph, before further
flight, repair the crack using a method approved in accordance with
the procedures specified in paragraph (n) of this AD. Repeat the
inspection of the unmodified areas thereafter at intervals not to
exceed 6,000 flight cycles.
Note 2: Boeing Alert Service Bulletin 747-53A2605, Revision 1,
dated May 27, 2010, refers to Section 51-10-02 of the Boeing 747-
400F Structural Repair Manual (SRM) and Section 51-10-01 of the
Boeing 747-100/200/300 SRM as additional sources of guidance for
removing small cracks and fatigue damage material from the existing
holes in the unmodified center section of the tension tie channels.
Where those SRM sections state that ``zero-timing must only be used
where specifically permitted in an SRM chapter-section-repair,''
this AD allows the zero-timing procedures specified in those SRM
sections.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(m) Actions done in accordance with Boeing Alert Service
Bulletin 747-53A2605,
[[Page 58726]]
dated October 8, 2009, before the effective date of this AD are
acceptable for compliance with the corresponding actions required by
paragraphs (j), (k), and (l) of this AD.
Alternative Methods of Compliance (AMOCs)
(n)(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 e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) Certain actions required by paragraph (g) of this AD are
approved as AMOCs for the requirements specified in paragraphs
(n)(4)(i), (n)(4)(ii), and (n)(4)(iii) of this AD. All provisions of
the referenced ADs in paragraphs (n)(4)(i), (n)(4)(ii), and
(n)(4)(iii) of this AD, including applicable post-modification
inspection thresholds, remain fully applicable and must be complied
with.
(i) Repairs or modifications of the aft tension tie channels
done in accordance with this AD are AMOCs for the repair
requirements of paragraph A. of AD 84-19-01, Amendment 39-4913 (49
FR 35365, September 17, 1984), and paragraphs (a)(2) and (b)(2) of
AD 94-13-06, Amendment 39-8946 (59 FR 32879, June 27, 1994).
(ii) The inspection requirements of this AD are AMOCs for the
post-modification inspection requirements of paragraph B. of AD 84-
19-01, Amendment 39-4913 (49 FR 35365, September 17, 1984), and
paragraph (b) of AD 94-13-06, Amendment 39-8946 (59 FR 32879, June
27, 1994).
(iii) The inspection requirements of this AD are AMOCs for the
inspections of Structural Significant Item (SSI) F-19A of Boeing
Supplemental Structural Inspection Document D6-35022, Revision G,
dated December 2000, as required by paragraphs (h) and (i) of AD
2004-07-22 R1, Amendment 39-15326 (73 FR 1052, January 7, 2008),
corrected on February 14, 2008 (73 FR 8589).
Related Information
(o) For more information about this AD, contact Steven Fox,
Senior Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle
ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6425; fax (425) 917-6590; e-mail: steven.fox@faa.gov.
(p) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
Issued in Renton, Washington, on September 14, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-24356 Filed 9-21-11; 8:45 am]
BILLING CODE 4910-13-P
