Airworthiness Directives; The Boeing Company Airplanes, 40481-40485 [2012-15894]
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Federal Register / Vol. 77, No. 132 / Tuesday, July 10, 2012 / Rules and Regulations
(c) Applicability
DEPARTMENT OF TRANSPORTATION
This AD applies only to Rolls-Royce
Corporation 250–C20, –C20B, and –C20R/2
turboshaft engines with 3rd stage turbine
wheel, part number (P/N) 23065818, and 4th
stage turbine wheel, P/N 23055944.
(d) Unsafe Condition
This AD was prompted by seven cases
reported of released turbine blades and
shrouds, which led to loss of power and
engine in-flight shutdowns. We are issuing
this AD to prevent failure of 3rd or 4th stage
turbine wheel blades which could cause
engine failure and damage to the airplane.
(e) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(1) Remove the 3rd stage turbine wheel,
P/N 23065818, and the 4th stage turbine
wheel, P/N 23055944, within 1,750-hours
since last inspection.
(2) Perform a one-time visual inspection
and a fluorescent penetrant inspection on the
3rd and 4th stage turbine wheels for cracks
at the trailing edge of the turbine blades near
the fillet at the rim.
(3) If any cracks in the trailing edge near
the rim are detected, do not return the wheel
to service.
(f) Alternative Methods of Compliance
(AMOCs)
The Manager, Chicago Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Use the procedures
found in 14 CFR 39.19 to make your request.
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(g) Related Information
(1) For more information about this AD,
contact John Tallarovic, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA,
2300 E. Devon Ave., Des Plaines, IL 60018;
phone: 847–294–8180; fax: 847–294–7834;
email: john.m.tallarovic@faa.gov.
(2) Rolls-Royce Corporation Alert
Commercial Engine Bulletin No. CEB–A–
1407, Revision 1, dated February 7, 2011 and
CEB–A–72–4098, Revision 1, dated February
7, 2011 (combined in one document) pertain
to the subject of this AD.
(3) For service information identified in
this AD, contact Rolls-Royce Corporation
Customer Support, P.O. Box 420,
Indianapolis, IN 46206–0420; phone:
888–255–4766 or 317–230–2720; fax: 317–
230–3381; email: helicoptercustsupp@rollsroyce.com, and Web site: www.rollsroyce.com.
(4) You may review copies of the
referenced 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.
Issued in Burlington, Massachusetts, on
June 25, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2012–16797 Filed 7–9–12; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0991; Directorate
Identifier 2010–NM–134–AD; Amendment
39–17110; AD 2012–13–08]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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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; 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
We are superseding an
existing airworthiness directive (AD) for
certain The Boeing Company 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. That 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 new AD requires, for
certain airplanes, modifying the tension
tie structure or tension tie and frame
structure at certain stations; and a postmodification 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 AD reduces the
compliance time and adds inspections
for certain airplanes. This AD was
prompted by reports that certain
airplanes have tension ties that are
susceptible to widespread fatigue
damage. This 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 issuing this AD to
prevent tension ties from becoming
severed or disconnected from the
frames, which could lead to rapid inflight decompression.
DATES: This AD is effective August 14,
2012.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of August 14, 2012.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of February 16, 2006 (71 FR
1947, January 12, 2006).
ADDRESSES: For service information
identified in this AD, contact Boeing
SUMMARY:
40481
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 address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: (425)
917–6428; fax: (425) 917–6590; email:
nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2006–01–07,
Amendment 39–14446 (71 FR 1947,
January 12, 2006). That AD applies to
the specified products. The NPRM
published in the Federal Register on
September 22, 2011 (76 FR 58722). That
NPRM proposed to continue to require
repetitive inspections for cracks of each
affected tension tie and of the
surrounding structure, and related
investigative and corrective actions if
necessary. For certain airplanes, that
NPRM proposed to require 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. That NPRM also
proposed to reduce the compliance time
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and add inspections for certain
airplanes.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (76 FR 58722,
September 22, 2011) and the FAA’s
response to each comment.
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Request to Revise Costs of Compliance
UPS requested that we revise the
Costs of Compliance section of the
NPRM (76 FR 58722, September 22,
2011). UPS explained that according to
paragraph 1.G. of Boeing Alert Service
Bulletin 747–53A2605, Revision 1,
dated May 27, 2010, the manpower
required to accomplish the modification
on all tension tie locations for UPS’s
Group 10 airplanes is 501 work-hours.
UPS also explained that according to
Boeing Alert Service Bulletin 747–
53A2605, Revision 1, dated May 27,
2010, the parts kits that are required to
accomplish the modification range from
$535,131 to $658,423. UPS reasoned
that based on Boeing’s labor estimate, a
labor rate of $85 per hour, and Boeing’s
current pricing, the cost to accomplish
the modification on each of UPS’s
airplanes would be approximately
$701,008.
We agree to revise the Costs of
Compliance section in the final rule to
align with the costs specified in the
service information. We have revised
the work-hours appropriately.
Request to Refer to the Service
Information
UPS requested that we revise
paragraphs (i)(2)(i) and (i)(2)(ii)(B) of the
NPRM (76 FR 58722, September 22,
2011) to, ‘‘* * * install the correct
configuration * * * 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 installation instructions:
Before further flight, install in
accordance with instructions approved
in accordance with the procedures
specified in paragraph (n) of this AD.’’
UPS explained that, while paragraphs
(i)(2)(i) and (i)(2)(ii)(B) of the NPRM
stipulate to install the correct
configuration using a method approved
in accordance with paragraph (n) of the
NPRM, Figure 22 of Boeing Alert
Service Bulletin 747–53A2502, Revision
1, dated June 17, 2010, provides the
correct configuration for installing the
tension tie attachments. UPS expressed
that they are concerned with the
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requirement to obtain AMOC approval
to install the correct configuration, as it
believes that this adds undue and
unnecessary burden on the operators
when correct configuration data already
exits.
We agree for the reasons stated by
UPS to revise the final rule to require
operators to install the correct
configuration in accordance with Boeing
Alert Service Bulletin 747–53A2502,
Revision 1, dated June 17, 2010. We
have revised paragraphs (i)(2)(i) and
(i)(2)(ii)(B) in this final rule accordingly.
Request To Include All Airplanes for
Actions Approved as AMOCs
UPS requested that we revise
paragraph (n)(4) of the NPRM (76 FR
58722, September 22, 2011) to refer to
paragraph (h) of the NPRM by
specifying ‘‘Certain actions required by
paragraphs (g) and (h) of this AD
* * *.’’ UPS explained that while
‘‘paragraph (n)(4) of the NPRM states
that certain actions required by
paragraph (g) of this AD are approved as
AMOCs for the requirements specified
in paragraph (n)(4)(i), (n)(4)(ii), and
(n)(4)(iii) of this AD,’’ paragraph (g) of
the NPRM applies only to Group 1 and
Groups 3 through 6 airplanes, as
identified in Boeing Alert Service
Bulletin 747–53A2502, Revision 1,
dated June 17, 2010. UPS expresses that
paragraph (n)(4)(iii) of the NPRM should
apply to all affected airplanes, not just
to Group 1 and Groups 3 through 6
airplanes.
We agree for the reasons stated by
UPS to revise paragraph (n)(4) of the
final rule to include reference to
paragraph (h) of the final rule. We have
revised paragraph (n)(4) of the final rule
accordingly.
Requests for Approval of Previous
AMOCs
UPS requested that, since the NPRM
(76 FR 58722, September 22, 2011)
supersedes AD 2006–01–07,
Amendment 39–14446 (71 FR 1947,
January 12, 2006), we revise the NPRM
to include a new paragraph that states
that AMOCs previously approved by AD
2006–01–07 should be approved as
AMOCs for the requirements of
paragraphs (g), (h), and (i) of the NPRM.
Boeing requested that we revise the
NPRM (76 FR 58722, September 22,
2011) to read, ‘‘For airplanes not
identified in Group 2 per Boeing Special
Attention Service Bulletin 747–
53A2502, Revision 1, dated June 17,
2011; AMOCs approved previously in
accordance with AD 2006–01–07,
Amendment 39–14446 (71 FR 1947,
January 12, 2006), are approved as
alternate methods of compliance with
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paragraph (g) of this AD.’’ Boeing
explained that Boeing Alert Service
Bulletin 747–53A2502, Revision 1,
dated June 17, 2010, reduces the
inspection thresholds and adds a onetime inspection for the Group 2
airplanes (Model 747–400F series
airplanes). All other airplane groups fall
within the requirements of the
superseded AD 2006–01–07, and
therefore, AMOCs provided in
paragraph (f) of AD 2006–01–07 are still
applicable. Boeing expressed that this
provision will reduce the resource
requirements of providing AMOC
approvals.
We partially agree to revise this AD to
allow certain AMOCs approved for AD
2006–01–07, Amendment 39–14446 (71
FR 1947, January 12, 2006). We agree to
allow AMOCs approved for AD 2006–
01–07 for the requirements of paragraph
(g) of this AD and have added paragraph
(n)(5) of this AD accordingly.
We also agree to allow AMOCs
approved according to AD 2006–01–07,
Amendment 39–14446 (71 FR 1947,
January 12, 2006), for the actions
required by paragraph (h) of this AD,
provided that the compliance times
specified in paragraph (h) of this AD are
met; the compliance times in paragraph
(h) of this AD are from those specified
in AD 2006–01–07. We have added
paragraph (n)(6) of this AD. We disagree
to allow AMOCs approved according to
AD 2006–01–07 for the requirements of
paragraph (i) of this AD, because the
actions in paragraph (i) of this AD are
new.
Additional Changes Made to This AD
We have revised the heading and
wording of paragraph (m) of this AD;
this revision has not affected the intent
of that paragraph.
We have redesignated Note 2 the
NPRM (76 FR 58722, September 22,
2011) as paragraph (l)(2) of this AD. We
have also redesignated paragraph (l) of
the NPRM as paragraph (l)(1) of this AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (76 FR
58722, September 22, 2011) for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (76 FR 58722,
September 22, 2011).
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We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of the AD.
Costs of Compliance
40483
We estimate the following costs to
comply with this AD:
We estimate that this AD affects 86
airplanes of U.S. registry.
ESTIMATED COSTS
Cost on U.S.
operators
Action
Labor cost
Parts cost
Cost per product
Inspection (required
by AD 2006–01–07,
Amendment 39–
14446 (71 FR 1947,
January 12, 2006)).
One-time inspection
(new action for
Group 2 airplanes).
Modification (new action).
8 per tension tie location, between 8 and
12 tension tie locations per airplane, depending on airplane configuration × $85
per hour = between $5,440 and $8,160.
$0 ..............................
Between $5,440 and
$8,160 per inspection cycle.
Between $467,840 and
$701,760 per inspection cycle.
6 × $85 per hour = $510 .............................
None .........................
$510 ..........................
$43,860.
Between 30 and 432 work-hours, depending on airplane configuration × $85 per
hour = between $2,550 and $36,720.
2 per tension tie location, between 8 and
12 tension tie locations per airplane, depending on airplane configuration × $85
per hour = between $1,360 and $2,040.
2 per tension tie location, between 8 and
12 tension tie locations per airplane, depending on airplane configuration × $85
per hour = between $1,360 and $2,040.
Between $18,657
and $658,423.
Between $21,207
and $695,143.
Between $1,823,802 and
$59,782,298.
None .........................
Between $1,360 and
$2,040, per inspection cycle.
Between $116,960 and
$175,440.
None .........................
Between $1,360 and
$2,040 per inspection cycles.
Between $116,960 and
$175,440.
Inspection for unmodified area (new action).
Inspection for modified area (new action).
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.
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Regulatory Findings
14:44 Jul 09, 2012
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
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(a) Effective Date
This airworthiness directive (AD) is
effective August 14, 2012.
(b) Affected ADs
This AD supersedes AD 2006–01–07,
Amendment 39–14446 (71 FR 1947, January
12, 2006).
(c) Applicability
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(d) Subject
PART 39—AIRWORTHINESS
DIRECTIVES
This AD was prompted by reports that
certain airplanes have tension ties that are
susceptible to widespread fatigue damage.
This 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. We are
issuing this AD to prevent tension ties from
becoming severed or disconnected from the
frames, which could lead to rapid in-flight
decompression.
1. The authority citation for part 39
continues to read as follows:
■
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
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(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.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2006–01–07, Amendment 39–14446 (71
FR 1947, January 12, 2006), and adding
the following new AD:
■
2012–13–08 The Boeing Company:
Amendment 39–17110; Docket No.
FAA–2011–0991; Directorate Identifier
2010–NM–134–AD.
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Air Transport Association (ATA) of
America Code 53: Fuselage.
(e) Unsafe Condition
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
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(g) Retained Actions With Reduced
Compliance Times for Certain Airplanes
This paragraph restates the requirements of
paragraph (f) of AD 2006–01–07, Amendment
39–14446 (71 FR 1947, January 12, 2006),
with reduced compliance time for certain
airplanes and revised service information.
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 the procedures specified in 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 to accomplish 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 (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 3,000 flight cycles
until the modification required by paragraph
(j) of this AD is accomplished.
(h) Retained Inspection for Group 2
Airplanes With Reduced Compliance Times
and Revised Service Information
This paragraph restates the requirements of
paragraph (f) of AD 2006–01–07, Amendment
39–14446 (71 FR 1947, January 12, 2006),
with reduced compliance time for certain
airplanes and revised service information.
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
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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 the procedures specified in 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 to accomplish the actions
required by this paragraph. 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 (the effective date of AD 2006–01–07,
Amendment 39–14446 (71 FR 1947, January
12, 2006)), whichever occurs later.
(2) For STA 720, 740, and 760: At the
earlier of the times specified in paragraph
(h)(2)(i) or (h)(2)(ii) of this AD.
(i) Before the accumulation of 17,000 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.
(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.
(i) New Requirement: One-Time Inspection
for Group 2 Airplanes
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.
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(2) If any incorrect configuration is found,
before further flight, do detailed and open
fastener-hole high frequency eddy current
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,
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
installation instructions, use 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
specified 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, 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 installation
instructions: Use a method approved in
accordance with the procedures specified in
paragraph (n) of this AD.
(j) Modification
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 the procedures specified in
paragraph (n) of this AD.
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10JYR1
Federal Register / Vol. 77, No. 132 / Tuesday, July 10, 2012 / Rules and Regulations
Note 1 to paragraph (j)(2) of this AD: For
airplanes identified in paragraph (j)(2) of this
AD, post-modification inspection guidance
may be included in an approved alternative
method of compliance (AMOC) for paragraph
(j)(2) of this AD.
(k) Post-Modification Inspection of the
Modified Areas
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 in
accordance 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.
(l) Post-Modification Repetitive Inspections
of the Unmodified Areas
(1) 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.
(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.
wreier-aviles on DSK6TPTVN1PROD with RULES
(m) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (j), (k), and
(l)(1) of this AD, if those actions were
performed before the effective date of this AD
using Boeing Alert Service Bulletin 747–
53A2605, dated October 8, 2009.
(n) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
VerDate Mar<15>2010
14:44 Jul 09, 2012
Jkt 226001
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 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 paragraphs
(g) and (h) 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 specified 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 February 14, 2008 (73 FR 8589).
(5) AMOCs approved previously in
accordance with AD 2006–01–07,
Amendment 39–14446 (71 FR 1947, January
12, 2006), are approved as AMOCs for the
corresponding provisions of paragraph (g) of
this AD.
(6) AMOCs approved previously in
accordance with AD 2006–01–07,
Amendment 39–14446 (71 FR 1947, January
12, 2006), are approved as AMOCs for the
corresponding repairs or modifications
required by paragraph (h) of this AD
provided that the actions are done within the
compliance times specified in paragraph (h)
of this AD. Compliance times in previously
approved AMOCs are not approved for
paragraph (h) of this AD.
(o) Related Information
For more information about this AD,
contact Nathan Weigand, Aerospace
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
40485
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: (425) 917–
6428; fax: (425) 917–6590; email:
nathan.p.weigand@faa.gov.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the following service information
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on August 14, 2012.
(i) Boeing Alert Service Bulletin 747–
53A2502, Revision 1, dated June 17, 2010.
(ii) Boeing Alert Service Bulletin 747–
53A2605, Revision 1, dated May 27, 2010.
(4) The following service info was
approved for IBR on February 16, 2006 (71
FR 1947, January 12, 2006).
(i) Boeing Special Attention Service
Bulletin 747–53A2502, dated April 21, 2005.
(5) 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; 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,
Washington. 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
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 June 19,
2012.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–15894 Filed 7–9–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0040; Directorate
Identifier 2011–NM–121–AD; Amendment
39–17108; AD 2012–13–06]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
E:\FR\FM\10JYR1.SGM
10JYR1
]]>Agencies
[Federal Register Volume 77, Number 132 (Tuesday, July 10, 2012)]
[Rules and Regulations]
[Pages 40481-40485]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-15894]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0991; Directorate Identifier 2010-NM-134-AD;
Amendment 39-17110; AD 2012-13-08]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain The Boeing Company 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. That 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 new AD requires, 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 AD reduces the compliance time and adds inspections for certain
airplanes. This AD was prompted by reports that certain airplanes have
tension ties that are susceptible to widespread fatigue damage. This 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 issuing this AD
to prevent tension ties from becoming severed or disconnected from the
frames, which could lead to rapid in-flight decompression.
DATES: This AD is effective August 14, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of August 14,
2012.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
February 16, 2006 (71 FR 1947, January 12, 2006).
ADDRESSES: 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; 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 AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone:
(425) 917-6428; fax: (425) 917-6590; email: nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2006-01-07, Amendment 39-14446 (71 FR 1947,
January 12, 2006). That AD applies to the specified products. The NPRM
published in the Federal Register on September 22, 2011 (76 FR 58722).
That NPRM proposed to continue to require repetitive inspections for
cracks of each affected tension tie and of the surrounding structure,
and related investigative and corrective actions if necessary. For
certain airplanes, that NPRM proposed to require 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. That NPRM also proposed to
reduce the compliance time
[[Page 40482]]
and add inspections for certain airplanes.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(76 FR 58722, September 22, 2011) and the FAA's response to each
comment.
Request to Revise Costs of Compliance
UPS requested that we revise the Costs of Compliance section of the
NPRM (76 FR 58722, September 22, 2011). UPS explained that according to
paragraph 1.G. of Boeing Alert Service Bulletin 747-53A2605, Revision
1, dated May 27, 2010, the manpower required to accomplish the
modification on all tension tie locations for UPS's Group 10 airplanes
is 501 work-hours. UPS also explained that according to Boeing Alert
Service Bulletin 747-53A2605, Revision 1, dated May 27, 2010, the parts
kits that are required to accomplish the modification range from
$535,131 to $658,423. UPS reasoned that based on Boeing's labor
estimate, a labor rate of $85 per hour, and Boeing's current pricing,
the cost to accomplish the modification on each of UPS's airplanes
would be approximately $701,008.
We agree to revise the Costs of Compliance section in the final
rule to align with the costs specified in the service information. We
have revised the work-hours appropriately.
Request to Refer to the Service Information
UPS requested that we revise paragraphs (i)(2)(i) and (i)(2)(ii)(B)
of the NPRM (76 FR 58722, September 22, 2011) to, ``* * * install the
correct configuration * * * 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 installation instructions: Before further flight, install in
accordance with instructions approved in accordance with the procedures
specified in paragraph (n) of this AD.'' UPS explained that, while
paragraphs (i)(2)(i) and (i)(2)(ii)(B) of the NPRM stipulate to install
the correct configuration using a method approved in accordance with
paragraph (n) of the NPRM, Figure 22 of Boeing Alert Service Bulletin
747-53A2502, Revision 1, dated June 17, 2010, provides the correct
configuration for installing the tension tie attachments. UPS expressed
that they are concerned with the requirement to obtain AMOC approval to
install the correct configuration, as it believes that this adds undue
and unnecessary burden on the operators when correct configuration data
already exits.
We agree for the reasons stated by UPS to revise the final rule to
require operators to install the correct configuration in accordance
with Boeing Alert Service Bulletin 747-53A2502, Revision 1, dated June
17, 2010. We have revised paragraphs (i)(2)(i) and (i)(2)(ii)(B) in
this final rule accordingly.
Request To Include All Airplanes for Actions Approved as AMOCs
UPS requested that we revise paragraph (n)(4) of the NPRM (76 FR
58722, September 22, 2011) to refer to paragraph (h) of the NPRM by
specifying ``Certain actions required by paragraphs (g) and (h) of this
AD * * *.'' UPS explained that while ``paragraph (n)(4) of the NPRM
states that certain actions required by paragraph (g) of this AD are
approved as AMOCs for the requirements specified in paragraph
(n)(4)(i), (n)(4)(ii), and (n)(4)(iii) of this AD,'' paragraph (g) of
the NPRM applies only to Group 1 and Groups 3 through 6 airplanes, as
identified in Boeing Alert Service Bulletin 747-53A2502, Revision 1,
dated June 17, 2010. UPS expresses that paragraph (n)(4)(iii) of the
NPRM should apply to all affected airplanes, not just to Group 1 and
Groups 3 through 6 airplanes.
We agree for the reasons stated by UPS to revise paragraph (n)(4)
of the final rule to include reference to paragraph (h) of the final
rule. We have revised paragraph (n)(4) of the final rule accordingly.
Requests for Approval of Previous AMOCs
UPS requested that, since the NPRM (76 FR 58722, September 22,
2011) supersedes AD 2006-01-07, Amendment 39-14446 (71 FR 1947, January
12, 2006), we revise the NPRM to include a new paragraph that states
that AMOCs previously approved by AD 2006-01-07 should be approved as
AMOCs for the requirements of paragraphs (g), (h), and (i) of the NPRM.
Boeing requested that we revise the NPRM (76 FR 58722, September
22, 2011) to read, ``For airplanes not identified in Group 2 per Boeing
Special Attention Service Bulletin 747-53A2502, Revision 1, dated June
17, 2011; AMOCs approved previously in accordance with AD 2006-01-07,
Amendment 39-14446 (71 FR 1947, January 12, 2006), are approved as
alternate methods of compliance with paragraph (g) of this AD.'' Boeing
explained that Boeing Alert Service Bulletin 747-53A2502, Revision 1,
dated June 17, 2010, reduces the inspection thresholds and adds a one-
time inspection for the Group 2 airplanes (Model 747-400F series
airplanes). All other airplane groups fall within the requirements of
the superseded AD 2006-01-07, and therefore, AMOCs provided in
paragraph (f) of AD 2006-01-07 are still applicable. Boeing expressed
that this provision will reduce the resource requirements of providing
AMOC approvals.
We partially agree to revise this AD to allow certain AMOCs
approved for AD 2006-01-07, Amendment 39-14446 (71 FR 1947, January 12,
2006). We agree to allow AMOCs approved for AD 2006-01-07 for the
requirements of paragraph (g) of this AD and have added paragraph
(n)(5) of this AD accordingly.
We also agree to allow AMOCs approved according to AD 2006-01-07,
Amendment 39-14446 (71 FR 1947, January 12, 2006), for the actions
required by paragraph (h) of this AD, provided that the compliance
times specified in paragraph (h) of this AD are met; the compliance
times in paragraph (h) of this AD are from those specified in AD 2006-
01-07. We have added paragraph (n)(6) of this AD. We disagree to allow
AMOCs approved according to AD 2006-01-07 for the requirements of
paragraph (i) of this AD, because the actions in paragraph (i) of this
AD are new.
Additional Changes Made to This AD
We have revised the heading and wording of paragraph (m) of this
AD; this revision has not affected the intent of that paragraph.
We have redesignated Note 2 the NPRM (76 FR 58722, September 22,
2011) as paragraph (l)(2) of this AD. We have also redesignated
paragraph (l) of the NPRM as paragraph (l)(1) of this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (76 FR 58722, September 22, 2011) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (76 FR 58722, September 22, 2011).
[[Page 40483]]
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 86 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection (required by AD 2006- 8 per tension tie $0............... Between $5,440 Between $467,840
01-07, Amendment 39-14446 (71 location, between 8 and $8,160 per and $701,760 per
FR 1947, January 12, 2006)). and 12 tension tie inspection cycle. inspection
locations per cycle.
airplane, depending
on airplane
configuration x $85
per hour = between
$5,440 and $8,160.
One-time inspection (new action 6 x $85 per hour = None............. $510............. $43,860.
for Group 2 airplanes). $510.
Modification (new action)...... Between 30 and 432 Between $18,657 Between $21,207 Between
work-hours, depending and $658,423. and $695,143. $1,823,802 and
on airplane $59,782,298.
configuration x $85
per hour = between
$2,550 and $36,720.
Inspection for unmodified area 2 per tension tie None............. Between $1,360 Between $116,960
(new action). location, between 8 and $2,040, per and $175,440.
and 12 tension tie inspection cycle.
locations per
airplane, depending
on airplane
configuration x $85
per hour = between
$1,360 and $2,040.
Inspection for modified area 2 per tension tie None............. Between $1,360 Between $116,960
(new action). location, between 8 and $2,040 per and $175,440.
and 12 tension tie inspection
locations per cycles.
airplane, depending
on airplane
configuration x $85
per hour = between
$1,360 and $2,040.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2006-01-07, Amendment 39-14446 (71 FR 1947, January 12, 2006), and
adding the following new AD:
2012-13-08 The Boeing Company: Amendment 39-17110; Docket No. FAA-
2011-0991; Directorate Identifier 2010-NM-134-AD.
(a) Effective Date
This airworthiness directive (AD) is effective August 14, 2012.
(b) Affected ADs
This AD supersedes AD 2006-01-07, Amendment 39-14446 (71 FR
1947, January 12, 2006).
(c) Applicability
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.
(d) Subject
Air Transport Association (ATA) of America Code 53: Fuselage.
(e) Unsafe Condition
This AD was prompted by reports that certain airplanes have
tension ties that are susceptible to widespread fatigue damage. This
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. We are issuing this AD to prevent tension ties from
becoming severed or disconnected from the frames, which could lead
to rapid in-flight decompression.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
[[Page 40484]]
(g) Retained Actions With Reduced Compliance Times for Certain
Airplanes
This paragraph restates the requirements of paragraph (f) of AD
2006-01-07, Amendment 39-14446 (71 FR 1947, January 12, 2006), with
reduced compliance time for certain airplanes and revised service
information. 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 the procedures specified in 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
to accomplish 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 (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
3,000 flight cycles until the modification required by paragraph (j)
of this AD is accomplished.
(h) Retained Inspection for Group 2 Airplanes With Reduced Compliance
Times and Revised Service Information
This paragraph restates the requirements of paragraph (f) of AD
2006-01-07, Amendment 39-14446 (71 FR 1947, January 12, 2006), with
reduced compliance time for certain airplanes and revised service
information. 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 the procedures specified in 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
to accomplish the actions required by this paragraph. 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 (the effective date of AD 2006-01-07, Amendment 39-14446
(71 FR 1947, January 12, 2006)), whichever occurs later.
(2) For STA 720, 740, and 760: At the earlier of the times
specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD.
(i) Before the accumulation of 17,000 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.
(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.
(i) New Requirement: One-Time Inspection for Group 2 Airplanes
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 high frequency eddy
current 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, 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 installation instructions, use 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
specified 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, 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 installation instructions:
Use a method approved in accordance with the procedures specified in
paragraph (n) of this AD.
(j) Modification
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 the
procedures specified in paragraph (n) of this AD.
[[Page 40485]]
Note 1 to paragraph (j)(2) of this AD: For airplanes identified
in paragraph (j)(2) of this AD, post-modification inspection
guidance may be included in an approved alternative method of
compliance (AMOC) for paragraph (j)(2) of this AD.
(k) Post-Modification Inspection of the Modified Areas
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 in accordance
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.
(l) Post-Modification Repetitive Inspections of the Unmodified Areas
(1) 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.
(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.
(m) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (j), (k), and (l)(1) of this AD, if those actions were
performed before the effective date of this AD using Boeing Alert
Service Bulletin 747-53A2605, dated October 8, 2009.
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: 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 paragraphs (g) and (h) 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 specified 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 February 14, 2008 (73 FR 8589).
(5) AMOCs approved previously in accordance with AD 2006-01-07,
Amendment 39-14446 (71 FR 1947, January 12, 2006), are approved as
AMOCs for the corresponding provisions of paragraph (g) of this AD.
(6) AMOCs approved previously in accordance with AD 2006-01-07,
Amendment 39-14446 (71 FR 1947, January 12, 2006), are approved as
AMOCs for the corresponding repairs or modifications required by
paragraph (h) of this AD provided that the actions are done within
the compliance times specified in paragraph (h) of this AD.
Compliance times in previously approved AMOCs are not approved for
paragraph (h) of this AD.
(o) Related Information
For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: (425) 917-6428; fax: (425) 917-6590; email:
nathan.p.weigand@faa.gov.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the following service
information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
August 14, 2012.
(i) Boeing Alert Service Bulletin 747-53A2502, Revision 1, dated
June 17, 2010.
(ii) Boeing Alert Service Bulletin 747-53A2605, Revision 1,
dated May 27, 2010.
(4) The following service info was approved for IBR on February
16, 2006 (71 FR 1947, January 12, 2006).
(i) Boeing Special Attention Service Bulletin 747-53A2502, dated
April 21, 2005. (5) 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; 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,
Washington. 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 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 June 19, 2012.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-15894 Filed 7-9-12; 8:45 am]
BILLING CODE 4910-13-P
