Airworthiness Directives; The Boeing Company Airplanes, 60891-60896 [2012-24412]
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Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations
instructions: Before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (k) of
this AD.
(j) Terminating Action
Replacing the STA 908 upper butt strap
and doing all applicable related investigative
and corrective actions, in accordance with
Part 4, Part 5, and Part 6, of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–53–
1313, dated November 3, 2011, except as
provided by paragraph (i)(2) of this AD,
terminates the inspections and chemical spot
test required by this AD.
(k) 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-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.
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(l) Related Information
For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: (425) 917–6447; fax: (425) 917–6590;
email: wayne.lockett@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Special Attention Service
Bulletin 737–53–1313, dated November 3,
2011.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
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(4) You may view this service information
at FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call (425) 227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
September 21, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–24280 Filed 10–4–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0492; Directorate
Identifier 2010–NM–126–AD; Amendment
39–17209; AD 2012–20–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
certain The Boeing Company Model 747
airplanes. That AD currently requires
repetitive visual inspections around the
bushings of the wing landing gear
(WLG) beam outboard end fittings for
corrosion, and rework if necessary; and
ultrasonic inspections for cracks of the
outboard end fittings of the WLG
support beams, and rework if necessary.
This new AD adds airplanes and adds
repetitive inspections of the outboard
end fitting of the left and right WLG
support beams for cracks and corrosion,
and corrective actions if necessary. This
AD was prompted by new reports of
corrosion damage to the end fittings of
the WLG support beams, and one report
of subsequent cracking in the end
fittings. We are issuing this AD to detect
and correct corrosion and subsequent
cracking in the outboard end fittings,
which could result in separation of the
fitting and damage to adjacent flight
control cables and hydraulic systems
and consequent reduced controllability
of the airplane.
DATES: This AD is effective November 9,
2012.
SUMMARY:
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60891
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of November 9, 2012.
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: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington
98057–3356; phone: (425) 917–6432;
fax: (425) 917–6590; email:
bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 89–15–07,
Amendment 39–6267 (54 FR 30009, July
18, 1989). That AD applies to the
specified products. The NPRM
published in the Federal Register on
May 31, 2012 (77 FR 32064). That
NPRM proposed to continue to require
repetitive visual inspections around the
bushings of the wing landing gear
(WLG) beam outboard end fittings for
corrosion, and rework if necessary; and
ultrasonic inspections for cracks of the
outboard end fittings of the WLG
support beams, and rework if necessary.
That NPRM also proposed to add
airplanes and repetitive inspections of
the outboard end fitting of the left and
right WLG support beams for cracks and
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Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations
corrosion, and corrective actions if
necessary.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (77 FR 32064,
May 31, 2012) and the FAA’s response
to each comment.
Request To Change Certain Language in
Paragraph (s) of the NPRM (77 FR
32064, May 31, 2012)
Boeing asked that the following
sentence be added to paragraph (s) of
the NPRM (77 FR 32064, May 31, 2012):
‘‘After accomplishing the repair or
change in accordance with Part 7 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 747–57A2331,
dated November 12, 2009, do the
applicable actions required by
paragraph (r) of this AD.’’ Boeing stated
that the follow-on inspections are
required after accomplishing the repair
or replacement in Part 7. Boeing added
that paragraph (q) of the NPRM contains
a similar requirement for Groups 1
through 5 airplanes.
We partially agree with the
commenter. We agree that the language
specified in paragraphs (q) and (s) of the
NPRM (77 FR 32064, May 31, 2012) is
inconsistent. However, we do not agree
to include the additional sentence in
paragraph (s) of this final rule because
it would continue to restate redundant
information, and may further confuse
operators. Therefore, we have removed
‘‘* * * do the applicable actions
required by paragraph (p) of this AD,’’
as was specified in paragraph (q) of the
NPRM, in order to provide consistency
between those related paragraphs.
Request To Include Certain Part
Numbers (P/Ns) in the NPRM (77 FR
32064, May 31, 2012)
Qantas Airways (QAN) asked that the
NPRM (77 FR 32064, May 31, 2012) be
reviewed to accurately capture all
approved part numbers for end fitting
replacements. QAN stated that, for its
Model 747–400 Configuration 6
airplanes, Boeing Alert Service Bulletin
747–57A2331, dated November 12,
2009, specifies that if a replacement
spare end fitting is required, an end
fitting assembly having P/N 112U1701–
1 is to be used for that replacement.
QAN noted that the parts page inventory
list from the original equipment
manufacturer (OEM) shows that P/N
112U1701–1 is no longer available and
has been replaced with P/N 112U2701–
7. QAN also noted that P/N 65B14473–
23 and P/N 65B14473–24 are no longer
available and have been replaced by P/
N 65B14473–33 and P/N 65B14473–34,
respectively. QAN added that these
replacement parts are not identified in
the referenced service information. QAN
also stated that, if any of the
replacement parts are used, it will be
forced to request an alternative method
of compliance (AMOC) from the OEM to
approve the use of an alternate part in
order to comply with the AD
requirements.
We acknowledge the commenter’s
concerns. However, as specified in the
NPRM (77 FR 32064, May 31, 2012),
since issuance of AD 89–15–07,
Amendment 39–6267 (54 FR 30009, July
18, 1989), corrosion occurred again at
the lug bore and bushing interface
because moisture continued to develop
in that area due to exposure of the end
fittings to environmental conditions.
Subsequently, cracks occurred at the
corroded areas of the end fittings;
therefore, the unsafe condition specified
in the existing AD has not been
corrected. We find that issuing this AD
without further delay is necessary to
adequately address the identified unsafe
condition. Operators may submit a
request for approval of the replacement
part numbers (P/Ns) through an AMOC,
as specified in paragraph (u) of the AD.
We have not changed the AD in this
regard.
Request To Change Certain Paragraph
Identifiers in the NPRM (77 FR 32064,
May 31, 2012)
Boeing and Atlas Air asked that the
paragraph identifier in the last sentence
in paragraph (l) of the NPRM (77 FR
32064, May 31, 2012) be changed from
paragraph (j) to paragraph (p). Boeing
and Atlas Air stated that paragraph (j) of
the NPRM would not be applicable
since it applies to inspections of the end
fittings prior to accomplishing the repair
or replacement in Part 7 of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009. Atlas Air added
that paragraph (p) of the NPRM defines
the procedures for follow-on end fitting
inspections on which the repair or
replacement specified in Part 7 has been
done.
Boeing, Atlas Air, and UPS asked that
the paragraph identifier in the last
sentence in paragraph (n) of the NPRM
(77 FR 32064, May 31, 2012) be changed
from paragraph (m) to paragraph (r).
Boeing, Atlas Air, and UPS stated that
paragraph (m) of the NPRM applies to
inspections of the end fittings prior to
accomplishing the repair or replacement
in Part 7 of Boeing Alert Service
Bulletin 747–57A2331, dated November
12, 2009. Atlas Air added that paragraph
(r) of the NPRM defines the procedures
for follow-on end fitting inspections on
which the repair or replacement
specified in Part 7 has been done.
We agree with the commenters for the
reasons provided. We have changed the
paragraph identifiers in paragraphs (l)
and (n) of this AD accordingly.
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.
We also determined that these changes
will not increase the economic burden
on any operator or increase the scope of
the AD.
Explanation of Change to Costs of
Compliance
Since issuance of AD 89–15–07,
Amendment 39–6267 (54 FR 30009, July
18, 1989), we have increased the labor
rate used in the Costs of Compliance
from $40 per work-hour to $85 per
work-hour. The Costs of Compliance
information, below, reflects this
increase in the specified labor rate.
Costs of Compliance
We estimate that this AD affects 173
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Inspections [retained actions
from existing AD 89–15–07,
Amendment 39-6267 (54
FR 30009, July 18, 1989)].
10 work-hours × $85 per hour
= $850 per inspection cycle.
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Parts cost
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Cost per product
$0
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$850 per inspection cycle ......
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05OCR1
Cost on U.S. operators
$147,050 per inspection
cycle.
Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations
60893
ESTIMATED COSTS—Continued
Action
Inspections [new action] .........
Labor cost
Parts cost
Up to 67 work-hours × $85
per hour = $5,695 per inspection cycle, depending
on configuration.
We estimate the following costs to do
any necessary repairs/replacements that
Cost per product
$0
Cost on U.S. operators
Up to $5,695 per inspection
cycle, depending on configuration.
would be required based on the results
of the inspection. We have no way of
Up to $985,235 per inspection
cycle, depending on configuration.
determining the number of aircraft that
might need these repairs/replacements:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per product
Repair or replacement ...................
Up to 71 work-hours × $85 per
hour = $6,035, depending on
configuration.
Up to $26,436, depending on configuration.
Up to $32,471, depending on 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.
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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
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
89–15–07, Amendment 39–6267 (54 FR
30009, July 18, 1989), and adding the
following new AD:
■
2012–20–03 The Boeing Company:
Amendment 39–17209; Docket No.
FAA–2012–0492; Directorate Identifier
2010–NM–126–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective November 9, 2012.
(b) Affected ADs
This AD supersedes AD 89–15–07,
Amendment 39–6267 (54 FR 30009, July 18,
1989).
(c) Applicability
This AD applies to The Boeing Company
Model 747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–300,
747–400, 747–400D, 747–400F, 747SR, and
747SP series airplanes; certificated in any
category; as identified in Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
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(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by new reports of
corrosion damage to the end fittings of the
wing landing gear (WLG) support beams, and
one report of subsequent cracking in the end
fittings. We are issuing this AD to detect and
correct corrosion and subsequent cracking in
the outboard end fittings, which could result
in separation of the fitting and damage to
adjacent flight control cables and hydraulic
systems and consequent reduced
controllability of the airplane.
(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.
(g) Retained Repetitive Inspections With
Revised Compliance Times
This paragraph restates the requirements of
paragraphs A., B., C., and D., of AD 89–15–
07, Amendment 39–6267 (54 FR 30009, July
18, 1989) with revised compliance times. For
airplanes identified in Boeing Service
Bulletin 747–57–2244, Revision 1, dated July
28, 1988: Prior to the accumulation of 30,000
flight hours or 8 years in service, whichever
occurs first; or within the next 14 months
after August 22, 1989 (the effective date of
AD 89–15–07); whichever occurs later;
visually inspect around the fitting lug
bushings at the WLG beam outboard end
fittings for corrosion, and ultrasonically
inspect the WLG beam outboard end fittings
for cracks, in accordance with Boeing Service
Bulletin 747–57–2244, Revision 1, dated July
28, 1988. Accomplishing the initial
inspections required by paragraph (j) of this
AD terminates the inspections required by
this paragraph.
(1) If no cracking or corrosion is found,
repeat the inspections at intervals not to
exceed 18 months until paragraph (j) of this
AD has been accomplished.
(2) If cracking is found, prior to further
flight, remove the WLG beam outboard
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fitting, and rework, in accordance with
Boeing Service Bulletin 747–57–2244,
Revision 1, dated July 28, 1988.
(3) If only corrosion is found, within the
next 12 months, rework in accordance with
Boeing Service Bulletin 747–57–2244,
Revision 1, dated July 28, 1988. The
ultrasonic inspections for cracks required by
paragraph (g) of this AD must be
accomplished at intervals not to exceed 6
months until the rework is accomplished. For
any corrosion that is found after the effective
date of this AD, the rework must be done
before further flight.
(h) Retained Terminating Action
This paragraph restates the requirements of
paragraph E., of AD 89–15–07, Amendment
39–6267 (54 FR 30009, July 18, 1989).
Terminating action for the inspections
required by paragraph (g) of this AD consists
of rework of the WLG beam outboard fittings,
in accordance with Boeing Service Bulletin
747–57–2244, Revision 1, dated July 28,
1988.
(i) New Compliance Times for This AD
For all the actions identified in paragraphs
(j) through (t) of this AD, do the actions at
the applicable time specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–57A2331, dated November 12,
2009. Where paragraph 1.E., ‘‘Compliance’’ of
this service bulletin specifies a compliance
time relative to the original issue date of the
service bulletin, this AD requires compliance
within the specified compliance time after
the effective date of this AD.
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(j) New Repetitive Inspections for Groups 1
Through 5 Airplanes
For Groups 1 through 3 airplanes,
Configurations 1 and 2; and Groups 4 and 5
airplanes: Do detailed and ultrasonic
inspections of the end fittings for cracks and
corrosion, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(k) New Inspections for No Crack or
Corrosion Findings for Groups 1 Through 5
Airplanes
If no crack or corrosion is found during any
inspection required by paragraph (j) of this
AD, do either of the actions required by
paragraph (k)(1) or (k)(2) of this AD.
(1) Repeat the detailed and ultrasonic
inspections of the end fittings for cracks and
corrosion, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(2) Do a detailed inspection of the end
fittings for fillet seal damage and for cracks
and corrosion, in accordance with Part 2 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–57A2331, dated
November 12, 2009.
(i) If no fillet seal damage, crack, or
corrosion is found: Repeat the inspection
required by paragraph (k)(2) of this AD.
(ii) If any fillet seal damage is found, but
no crack or corrosion is found: Remove the
fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and
corrosion, in accordance with Part 2 of the
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Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (l) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and do detailed and
HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(1) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, and thereafter repeat the
inspections required by paragraph
(k)(2)(ii)(B) of this AD.
(2) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (l) of this AD.
(l) New Repair for Crack or Corrosion
Findings for Groups 1 Through 5 Airplanes
If any crack or corrosion is found during
any inspection required by paragraph (j) or
(k) of this AD: Repair or change the end
fitting, in accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009. After accomplishing the
repair or change in accordance with Part 7 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–57A2331, dated
November 12, 2009, do the applicable actions
required by paragraph (p) of this AD.
(m) New Repetitive Inspections and
Corrective Actions for Group 6 Airplanes
For Group 6 airplanes: Do a detailed
inspection of the end fittings for fillet seal
damage and for cracks and corrosion, in
accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(1) If no fillet seal damage, crack, or
corrosion is found: Do the detailed
inspection of the end fittings for fillet seal
damage and for cracks and corrosion, in
accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(i) If no fillet seal damage, crack, or
corrosion is found: Repeat the detailed
inspection required by paragraph (m)(1) of
this AD.
(ii) If any fillet seal damage is found, but
no crack or corrosion is found: Remove the
fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and
corrosion, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (n) of this AD.
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(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and do detailed and
HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(1) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (n) of this AD.
(2) If no crack or corrosion is found: Apply
corrosion inhibiting compound, in
accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, and thereafter repeat the
inspections required by paragraph
(m)(1)(ii)(B) of this AD.
(2) If any fillet seal damage is found, but
no crack or corrosion is found: Remove the
fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and
corrosion, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(i) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (n) of this AD.
(ii) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and do detailed and
HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with paragraph (n) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound, in
accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, and thereafter repeat the
inspections required by paragraph (m)(2)(ii)
of this AD.
(n) New Repair for Group 6 Airplanes
If any crack or corrosion is found during
any inspection required by paragraph (m) of
this AD: Repair or change the end fitting, in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009. After accomplishing the
repair or change in accordance with Part 7 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–57A2331, dated
November 12, 2009, do the applicable actions
required by paragraph (r) of this AD.
(o) New Optional Terminating Action for
Part 1, Part 2, and Part 3 Inspections
In lieu of doing Part 1, Part 2, or Part 3
inspections required by this AD: Repair or
change the end fitting, in accordance with
Part 7 of the Accomplishment Instructions of
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pmangrum on DSK3VPTVN1PROD with RULES
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009. After
accomplishing the repair or change in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, do the applicable actions
required by paragraphs (p) and (r) of this AD.
Doing the repair or change terminates the
Part 1, 2, or 3 inspections for that part only
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(p) New Follow-On End Fitting Inspection
for Groups 1 Through 5 Airplanes
For Groups 1 through 5 airplanes on which
the repair or change specified in Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, has been done: Do
detailed and ultrasonic inspections of the
end fittings for cracks and corrosion, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009. If no crack or corrosion
is found, do the actions required by either
paragraph (p)(1) or (p)(2) of this AD.
(1) Repeat the detailed and ultrasonic
inspections of the end fittings for cracks and
corrosion required by paragraph (p) of this
AD.
(2) Do a detailed inspection of each end
fitting for fillet seal damage, cracks, and
corrosion, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(i) If no fillet seal damage, crack, or
corrosion is found: Repeat the inspection
required by paragraph (p)(2) of this AD.
(ii) If any fillet seal damage is found, but
no crack or corrosion is found: Remove the
fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and
corrosion, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting, as required
by paragraph (q) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and do detailed and
HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(1) If any crack or corrosion is found:
Repair or change the end fitting, as required
by paragraph (q) of this AD.
(2) If no crack or corrosion is found: Apply
corrosion inhibiting compound, in
accordance with Part 6 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and repeat the detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
VerDate Mar<15>2010
15:07 Oct 04, 2012
Jkt 229001
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(q) New Repair for Groups 1 Through 5
Airplanes
If any crack or corrosion is found during
any inspection required by paragraph (p) of
this AD, repair or change the end fitting, in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(r) New Follow-On End Fitting Inspection for
Group 6 Airplanes
For Group 6 airplanes on which the repair
or change specified in Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, has been done: Do a
detailed inspection of the end fittings for
fillet seal damage, cracks, and corrosion, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(1) If no fillet seal damage, crack, or
corrosion is found: Do a detailed inspection
of each end fitting for fillet seal damage,
cracks, and corrosion, in accordance with
Part 5 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(i) If no fillet seal damage, crack, or
corrosion is found: Repeat the inspection
required by paragraph (r)(1) of this AD.
(ii) If any fillet seal damage is found, but
no crack or corrosion is found: Do detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
5 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting as required
by paragraph (s) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and repeat the detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(1) If any crack or corrosion is found:
Repair or change the end fitting, in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(2) If no crack or corrosion is found: Apply
corrosion inhibiting compound, in
accordance with Part 6 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and repeat the detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(2) If any fillet seal damage is found, but
no crack or corrosion is found: Do detailed
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
60895
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
4 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(i) If any crack or corrosion is found:
Repair or change the end fitting, as required
by paragraph (s) of this AD.
(ii) If no crack or corrosion is found: Apply
corrosion inhibiting compound on each end
fitting, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and do detailed and
HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(A) If any crack or corrosion is found:
Repair or change the end fitting, as required
by paragraph (s) of this AD.
(B) If no crack or corrosion is found: Apply
corrosion inhibiting compound, in
accordance with Part 6 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009; and repeat the detailed
and HFEC inspections of each end fitting for
cracks and corrosion, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009.
(s) New Repair for Group 6 Airplanes
If any crack or corrosion is found during
any inspection required by paragraph (r) of
this AD, repair or change the end fitting, in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009.
(t) New Optional Action for Part 4, Part 5,
and Part 6 Inspections
In lieu of doing Part 4, Part 5, or Part 6
inspections required by this AD: Repair or
change the end fitting, in accordance with
Part 7 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2331,
dated November 12, 2009. After
accomplishing the repair or change in
accordance with Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2331, dated
November 12, 2009, do the applicable actions
required by paragraphs (p) and (r) of this AD.
(u) 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-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
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Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 89–15–07, Amendment
39–6267 (54 FR 30009, July 18, 1989), are
approved as AMOCs for the corresponding
requirements of this AD.
(1) For more information about this AD,
contact Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; phone: (425) 917–6432; fax: (425) 917–
6590; email: bill.ashforth@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, 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.
pmangrum on DSK3VPTVN1PROD with RULES
(w) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 747–
57A2331, dated November 12, 2009.
(ii) Boeing Service Bulletin 747–57–2244,
Revision 1, dated July 28, 1988.
(3) 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.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
15:07 Oct 04, 2012
[FR Doc. 2012–24412 Filed 10–4–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Part 117
[Docket No. USCG–2012–0888]
(v) Related Information
VerDate Mar<15>2010
Issued in Renton, Washington, on
September 26, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
Jkt 229001
Drawbridge Operation Regulation;
Delaware River, Between Burlington,
NJ and Bristol, PA
Coast Guard, DHS.
Notice of temporary deviation
from regulations.
AGENCY:
ACTION:
The Commander, Fifth Coast
Guard District, has issued a temporary
deviation from the regulations
governing the operation of the
Burlington-Bristol Bridge on Route 413,
across the Delaware River, at mile 117.8,
between Burlington, NJ and Bristol, PA.
This deviation restricts the operation of
the draw span in order to facilitate the
adjustment of the operating lift cables.
DATES: This deviation is effective from
7 a.m. on October 30, 2012 to 3 p.m. on
November 1, 2012.
ADDRESSES: Documents mentioned in
this preamble as being available in the
docket are part of docket USCG–2012–
0888 and are available online by going
to https://www.regulations.gov, inserting
USCG–2012–0888 in the ‘‘Keyword’’
box and then clicking ‘‘Search’’. They
are also available for inspection or
copying at the Docket Management
Facility (M–30), U.S. Department of
Transportation, 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 FURTHER INFORMATION CONTACT: If
you have questions on this rule, call or
email Terrance Knowles, Environmental
Protection Specialist, Fifth Coast Guard
District; telephone 757–398–6587, email
Terrance.A.Knowles@uscg.mil. If you
have questions on viewing the docket,
call Renee V. Wright, Program Manager,
Docket Operations, telephone 202–366–
9826.
SUPPLEMENTARY INFORMATION: The
Burlington County Bridge Commission,
who owns and operates this vertical-lift
type drawbridge, has requested a
temporary deviation from the current
SUMMARY:
PO 00000
Frm 00014
Fmt 4700
Sfmt 9990
operating regulations set out in 33 CFR
117.5 and 117.716(b) to facilitate the
adjustment of the operational lift cables.
The Burlington-Bristol Bridge on
Route 413, at mile 117.8, across the
Delaware River, between Burlington NJ
and Bristol PA, has a vertical clearance
in the closed position to vessels of 62
feet above mean high water.
Under the regular operating schedule
the bridge opens on signal as required
by 33 CFR 117.5 and the opening of a
bridge may not be delayed more than
five minutes for a highway bridge, after
the signal to open is given as required
by 33 CFR 117.716(b).
Under this temporary deviation, the
Burlington-Bristol Bridge will be closed
to navigation and unable to open on
signal each day from 7 a.m. until 3 p.m.
on October 30, 2012 and November 1,
2012.
Vessels that can pass under the bridge
without a drawbridge opening may do
so at all times. There are no alternate
routes for vessels transiting this section
of the Delaware River.
There are approximately four to six
vessels per week from four facilities
whose vertical clearance surpasses the
closed bridge position, requiring an
opening of the draw span. The Coast
Guard has coordinated this replacement
work with the Mariners’ Advisory
Committee for the Bay & River
Delaware, and will inform the other
users of the waterway through our Local
and Broadcast Notices to Mariners of the
closure periods for the bridge so that
vessels can arrange their transits to
minimize any impact caused by the
temporary deviation. The bridge will
not be able to open in an emergency
during lift cable tension adjustments.
In accordance with 33 CFR 117.35(e),
the drawbridge must return to its regular
operating schedule immediately at the
end of the designated time period. This
deviation from the operating regulations
is authorized under 33 CFR 117.35.
Dated: September 25, 2012.
Waverly W. Gregory, Jr.,
Bridge Program Manager, Fifth Coast Guard
District.
[FR Doc. 2012–24598 Filed 10–4–12; 8:45 am]
BILLING CODE 9110–04–P
E:\FR\FM\05OCR1.SGM
05OCR1
]]>Agencies
[Federal Register Volume 77, Number 194 (Friday, October 5, 2012)]
[Rules and Regulations]
[Pages 60891-60896]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-24412]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0492; Directorate Identifier 2010-NM-126-AD;
Amendment 39-17209; AD 2012-20-03]
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 airplanes. That AD currently
requires repetitive visual inspections around the bushings of the wing
landing gear (WLG) beam outboard end fittings for corrosion, and rework
if necessary; and ultrasonic inspections for cracks of the outboard end
fittings of the WLG support beams, and rework if necessary. This new AD
adds airplanes and adds repetitive inspections of the outboard end
fitting of the left and right WLG support beams for cracks and
corrosion, and corrective actions if necessary. This AD was prompted by
new reports of corrosion damage to the end fittings of the WLG support
beams, and one report of subsequent cracking in the end fittings. We
are issuing this AD to detect and correct corrosion and subsequent
cracking in the outboard end fittings, which could result in separation
of the fitting and damage to adjacent flight control cables and
hydraulic systems and consequent reduced controllability of the
airplane.
DATES: This AD is effective November 9, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of November 9,
2012.
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: Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-
6432; fax: (425) 917-6590; email: bill.ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 89-15-07, Amendment 39-6267 (54 FR 30009, July
18, 1989). That AD applies to the specified products. The NPRM
published in the Federal Register on May 31, 2012 (77 FR 32064). That
NPRM proposed to continue to require repetitive visual inspections
around the bushings of the wing landing gear (WLG) beam outboard end
fittings for corrosion, and rework if necessary; and ultrasonic
inspections for cracks of the outboard end fittings of the WLG support
beams, and rework if necessary. That NPRM also proposed to add
airplanes and repetitive inspections of the outboard end fitting of the
left and right WLG support beams for cracks and
[[Page 60892]]
corrosion, and corrective actions if necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 32064, May 31, 2012) and the FAA's response to each comment.
Request To Change Certain Language in Paragraph (s) of the NPRM (77 FR
32064, May 31, 2012)
Boeing asked that the following sentence be added to paragraph (s)
of the NPRM (77 FR 32064, May 31, 2012): ``After accomplishing the
repair or change in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009, do the applicable actions required by paragraph (r)
of this AD.'' Boeing stated that the follow-on inspections are required
after accomplishing the repair or replacement in Part 7. Boeing added
that paragraph (q) of the NPRM contains a similar requirement for
Groups 1 through 5 airplanes.
We partially agree with the commenter. We agree that the language
specified in paragraphs (q) and (s) of the NPRM (77 FR 32064, May 31,
2012) is inconsistent. However, we do not agree to include the
additional sentence in paragraph (s) of this final rule because it
would continue to restate redundant information, and may further
confuse operators. Therefore, we have removed ``* * * do the applicable
actions required by paragraph (p) of this AD,'' as was specified in
paragraph (q) of the NPRM, in order to provide consistency between
those related paragraphs.
Request To Include Certain Part Numbers (P/Ns) in the NPRM (77 FR
32064, May 31, 2012)
Qantas Airways (QAN) asked that the NPRM (77 FR 32064, May 31,
2012) be reviewed to accurately capture all approved part numbers for
end fitting replacements. QAN stated that, for its Model 747-400
Configuration 6 airplanes, Boeing Alert Service Bulletin 747-57A2331,
dated November 12, 2009, specifies that if a replacement spare end
fitting is required, an end fitting assembly having P/N 112U1701-1 is
to be used for that replacement. QAN noted that the parts page
inventory list from the original equipment manufacturer (OEM) shows
that P/N 112U1701-1 is no longer available and has been replaced with
P/N 112U2701-7. QAN also noted that P/N 65B14473-23 and P/N 65B14473-24
are no longer available and have been replaced by P/N 65B14473-33 and
P/N 65B14473-34, respectively. QAN added that these replacement parts
are not identified in the referenced service information. QAN also
stated that, if any of the replacement parts are used, it will be
forced to request an alternative method of compliance (AMOC) from the
OEM to approve the use of an alternate part in order to comply with the
AD requirements.
We acknowledge the commenter's concerns. However, as specified in
the NPRM (77 FR 32064, May 31, 2012), since issuance of AD 89-15-07,
Amendment 39-6267 (54 FR 30009, July 18, 1989), corrosion occurred
again at the lug bore and bushing interface because moisture continued
to develop in that area due to exposure of the end fittings to
environmental conditions. Subsequently, cracks occurred at the corroded
areas of the end fittings; therefore, the unsafe condition specified in
the existing AD has not been corrected. We find that issuing this AD
without further delay is necessary to adequately address the identified
unsafe condition. Operators may submit a request for approval of the
replacement part numbers (P/Ns) through an AMOC, as specified in
paragraph (u) of the AD. We have not changed the AD in this regard.
Request To Change Certain Paragraph Identifiers in the NPRM (77 FR
32064, May 31, 2012)
Boeing and Atlas Air asked that the paragraph identifier in the
last sentence in paragraph (l) of the NPRM (77 FR 32064, May 31, 2012)
be changed from paragraph (j) to paragraph (p). Boeing and Atlas Air
stated that paragraph (j) of the NPRM would not be applicable since it
applies to inspections of the end fittings prior to accomplishing the
repair or replacement in Part 7 of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009. Atlas Air added that paragraph (p) of
the NPRM defines the procedures for follow-on end fitting inspections
on which the repair or replacement specified in Part 7 has been done.
Boeing, Atlas Air, and UPS asked that the paragraph identifier in
the last sentence in paragraph (n) of the NPRM (77 FR 32064, May 31,
2012) be changed from paragraph (m) to paragraph (r). Boeing, Atlas
Air, and UPS stated that paragraph (m) of the NPRM applies to
inspections of the end fittings prior to accomplishing the repair or
replacement in Part 7 of Boeing Alert Service Bulletin 747-57A2331,
dated November 12, 2009. Atlas Air added that paragraph (r) of the NPRM
defines the procedures for follow-on end fitting inspections on which
the repair or replacement specified in Part 7 has been done.
We agree with the commenters for the reasons provided. We have
changed the paragraph identifiers in paragraphs (l) and (n) of this AD
accordingly.
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. We also determined that
these changes will not increase the economic burden on any operator or
increase the scope of the AD.
Explanation of Change to Costs of Compliance
Since issuance of AD 89-15-07, Amendment 39-6267 (54 FR 30009, July
18, 1989), we have increased the labor rate used in the Costs of
Compliance from $40 per work-hour to $85 per work-hour. The Costs of
Compliance information, below, reflects this increase in the specified
labor rate.
Costs of Compliance
We estimate that this AD affects 173 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
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions 10 work-hours x $85 $0 $850 per inspection $147,050 per
from existing AD 89-15-07, per hour = $850 cycle. inspection cycle.
Amendment 39[dash]6267 (54 FR per inspection
30009, July 18, 1989)]. cycle.
[[Page 60893]]
Inspections [new action]......... Up to 67 work-hours $0 Up to $5,695 per Up to $985,235 per
x $85 per hour = inspection cycle, inspection cycle,
$5,695 per depending on depending on
inspection cycle, configuration. configuration.
depending on
configuration.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs/
replacements that would be required based on the results of the
inspection. We have no way of determining the number of aircraft that
might need these repairs/replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair or replacement................ Up to 71 work-hours x Up to $26,436, Up to $32,471,
$85 per hour = $6,035, depending on depending on
depending on configuration. configuration.
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 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)
89-15-07, Amendment 39-6267 (54 FR 30009, July 18, 1989), and adding
the following new AD:
2012-20-03 The Boeing Company: Amendment 39-17209; Docket No. FAA-
2012-0492; Directorate Identifier 2010-NM-126-AD.
(a) Effective Date
This airworthiness directive (AD) is effective November 9, 2012.
(b) Affected ADs
This AD supersedes AD 89-15-07, Amendment 39-6267 (54 FR 30009,
July 18, 1989).
(c) Applicability
This AD applies to The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, 747SR, and 747SP series airplanes; certificated in
any category; as identified in Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by new reports of corrosion damage to the
end fittings of the wing landing gear (WLG) support beams, and one
report of subsequent cracking in the end fittings. We are issuing
this AD to detect and correct corrosion and subsequent cracking in
the outboard end fittings, which could result in separation of the
fitting and damage to adjacent flight control cables and hydraulic
systems and consequent reduced controllability of the airplane.
(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.
(g) Retained Repetitive Inspections With Revised Compliance Times
This paragraph restates the requirements of paragraphs A., B.,
C., and D., of AD 89-15-07, Amendment 39-6267 (54 FR 30009, July 18,
1989) with revised compliance times. For airplanes identified in
Boeing Service Bulletin 747-57-2244, Revision 1, dated July 28,
1988: Prior to the accumulation of 30,000 flight hours or 8 years in
service, whichever occurs first; or within the next 14 months after
August 22, 1989 (the effective date of AD 89-15-07); whichever
occurs later; visually inspect around the fitting lug bushings at
the WLG beam outboard end fittings for corrosion, and ultrasonically
inspect the WLG beam outboard end fittings for cracks, in accordance
with Boeing Service Bulletin 747-57-2244, Revision 1, dated July 28,
1988. Accomplishing the initial inspections required by paragraph
(j) of this AD terminates the inspections required by this
paragraph.
(1) If no cracking or corrosion is found, repeat the inspections
at intervals not to exceed 18 months until paragraph (j) of this AD
has been accomplished.
(2) If cracking is found, prior to further flight, remove the
WLG beam outboard
[[Page 60894]]
fitting, and rework, in accordance with Boeing Service Bulletin 747-
57-2244, Revision 1, dated July 28, 1988.
(3) If only corrosion is found, within the next 12 months,
rework in accordance with Boeing Service Bulletin 747-57-2244,
Revision 1, dated July 28, 1988. The ultrasonic inspections for
cracks required by paragraph (g) of this AD must be accomplished at
intervals not to exceed 6 months until the rework is accomplished.
For any corrosion that is found after the effective date of this AD,
the rework must be done before further flight.
(h) Retained Terminating Action
This paragraph restates the requirements of paragraph E., of AD
89-15-07, Amendment 39-6267 (54 FR 30009, July 18, 1989).
Terminating action for the inspections required by paragraph (g) of
this AD consists of rework of the WLG beam outboard fittings, in
accordance with Boeing Service Bulletin 747-57-2244, Revision 1,
dated July 28, 1988.
(i) New Compliance Times for This AD
For all the actions identified in paragraphs (j) through (t) of
this AD, do the actions at the applicable time specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009. Where paragraph 1.E.,
``Compliance'' of this service bulletin specifies a compliance time
relative to the original issue date of the service bulletin, this AD
requires compliance within the specified compliance time after the
effective date of this AD.
(j) New Repetitive Inspections for Groups 1 Through 5 Airplanes
For Groups 1 through 3 airplanes, Configurations 1 and 2; and
Groups 4 and 5 airplanes: Do detailed and ultrasonic inspections of
the end fittings for cracks and corrosion, in accordance with Part 1
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(k) New Inspections for No Crack or Corrosion Findings for Groups 1
Through 5 Airplanes
If no crack or corrosion is found during any inspection required
by paragraph (j) of this AD, do either of the actions required by
paragraph (k)(1) or (k)(2) of this AD.
(1) Repeat the detailed and ultrasonic inspections of the end
fittings for cracks and corrosion, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(2) Do a detailed inspection of the end fittings for fillet seal
damage and for cracks and corrosion, in accordance with Part 2 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(i) If no fillet seal damage, crack, or corrosion is found:
Repeat the inspection required by paragraph (k)(2) of this AD.
(ii) If any fillet seal damage is found, but no crack or
corrosion is found: Remove the fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 2 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (l) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 2
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(1) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 3
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009, and thereafter repeat the
inspections required by paragraph (k)(2)(ii)(B) of this AD.
(2) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (l) of this AD.
(l) New Repair for Crack or Corrosion Findings for Groups 1 Through 5
Airplanes
If any crack or corrosion is found during any inspection
required by paragraph (j) or (k) of this AD: Repair or change the
end fitting, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009. After accomplishing the repair or change in
accordance with Part 7 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009, do the
applicable actions required by paragraph (p) of this AD.
(m) New Repetitive Inspections and Corrective Actions for Group 6
Airplanes
For Group 6 airplanes: Do a detailed inspection of the end
fittings for fillet seal damage and for cracks and corrosion, in
accordance with Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(1) If no fillet seal damage, crack, or corrosion is found: Do
the detailed inspection of the end fittings for fillet seal damage
and for cracks and corrosion, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(i) If no fillet seal damage, crack, or corrosion is found:
Repeat the detailed inspection required by paragraph (m)(1) of this
AD.
(ii) If any fillet seal damage is found, but no crack or
corrosion is found: Remove the fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 2 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (n) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 2
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(1) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (n) of this AD.
(2) If no crack or corrosion is found: Apply corrosion
inhibiting compound, in accordance with Part 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009, and thereafter repeat the inspections required by
paragraph (m)(1)(ii)(B) of this AD.
(2) If any fillet seal damage is found, but no crack or
corrosion is found: Remove the fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(i) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (n) of this AD.
(ii) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 1
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with paragraph (n) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound, in accordance with Part 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009, and thereafter repeat the inspections required by
paragraph (m)(2)(ii) of this AD.
(n) New Repair for Group 6 Airplanes
If any crack or corrosion is found during any inspection
required by paragraph (m) of this AD: Repair or change the end
fitting, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009. After accomplishing the repair or change in
accordance with Part 7 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009, do the
applicable actions required by paragraph (r) of this AD.
(o) New Optional Terminating Action for Part 1, Part 2, and Part 3
Inspections
In lieu of doing Part 1, Part 2, or Part 3 inspections required
by this AD: Repair or change the end fitting, in accordance with
Part 7 of the Accomplishment Instructions of
[[Page 60895]]
Boeing Alert Service Bulletin 747-57A2331, dated November 12, 2009.
After accomplishing the repair or change in accordance with Part 7
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009, do the applicable actions
required by paragraphs (p) and (r) of this AD. Doing the repair or
change terminates the Part 1, 2, or 3 inspections for that part only
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(p) New Follow-On End Fitting Inspection for Groups 1 Through 5
Airplanes
For Groups 1 through 5 airplanes on which the repair or change
specified in Part 7 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009, has
been done: Do detailed and ultrasonic inspections of the end
fittings for cracks and corrosion, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009. If no crack or corrosion is found,
do the actions required by either paragraph (p)(1) or (p)(2) of this
AD.
(1) Repeat the detailed and ultrasonic inspections of the end
fittings for cracks and corrosion required by paragraph (p) of this
AD.
(2) Do a detailed inspection of each end fitting for fillet seal
damage, cracks, and corrosion, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(i) If no fillet seal damage, crack, or corrosion is found:
Repeat the inspection required by paragraph (p)(2) of this AD.
(ii) If any fillet seal damage is found, but no crack or
corrosion is found: Remove the fillet seal, and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 5 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting, as required by paragraph (q) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 5
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 6 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(1) If any crack or corrosion is found: Repair or change the end
fitting, as required by paragraph (q) of this AD.
(2) If no crack or corrosion is found: Apply corrosion
inhibiting compound, in accordance with Part 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009; and repeat the detailed and HFEC inspections of
each end fitting for cracks and corrosion, in accordance with Part 6
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(q) New Repair for Groups 1 Through 5 Airplanes
If any crack or corrosion is found during any inspection
required by paragraph (p) of this AD, repair or change the end
fitting, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009.
(r) New Follow-On End Fitting Inspection for Group 6 Airplanes
For Group 6 airplanes on which the repair or change specified in
Part 7 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2331, dated November 12, 2009, has been done: Do a
detailed inspection of the end fittings for fillet seal damage,
cracks, and corrosion, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(1) If no fillet seal damage, crack, or corrosion is found: Do a
detailed inspection of each end fitting for fillet seal damage,
cracks, and corrosion, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(i) If no fillet seal damage, crack, or corrosion is found:
Repeat the inspection required by paragraph (r)(1) of this AD.
(ii) If any fillet seal damage is found, but no crack or
corrosion is found: Do detailed and HFEC inspections of each end
fitting for cracks and corrosion, in accordance with Part 5 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting as required by paragraph (s) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 5
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and repeat the detailed and
HFEC inspections of each end fitting for cracks and corrosion, in
accordance with Part 6 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(1) If any crack or corrosion is found: Repair or change the end
fitting, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009.
(2) If no crack or corrosion is found: Apply corrosion
inhibiting compound, in accordance with Part 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009; and repeat the detailed and HFEC inspections of
each end fitting for cracks and corrosion, in accordance with Part 6
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(2) If any fillet seal damage is found, but no crack or
corrosion is found: Do detailed and HFEC inspections of each end
fitting for cracks and corrosion, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2331, dated November 12, 2009.
(i) If any crack or corrosion is found: Repair or change the end
fitting, as required by paragraph (s) of this AD.
(ii) If no crack or corrosion is found: Apply corrosion
inhibiting compound on each end fitting, in accordance with Part 4
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009; and do detailed and HFEC
inspections of each end fitting for cracks and corrosion, in
accordance with Part 6 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2331, dated November 12, 2009.
(A) If any crack or corrosion is found: Repair or change the end
fitting, as required by paragraph (s) of this AD.
(B) If no crack or corrosion is found: Apply corrosion
inhibiting compound, in accordance with Part 6 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009; and repeat the detailed and HFEC inspections of
each end fitting for cracks and corrosion, in accordance with Part 6
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2331, dated November 12, 2009.
(s) New Repair for Group 6 Airplanes
If any crack or corrosion is found during any inspection
required by paragraph (r) of this AD, repair or change the end
fitting, in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009.
(t) New Optional Action for Part 4, Part 5, and Part 6 Inspections
In lieu of doing Part 4, Part 5, or Part 6 inspections required
by this AD: Repair or change the end fitting, in accordance with
Part 7 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2331, dated November 12, 2009. After accomplishing
the repair or change in accordance with Part 7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2331, dated
November 12, 2009, do the applicable actions required by paragraphs
(p) and (r) of this AD.
(u) 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
[[Page 60896]]
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 89-15-07,
Amendment 39-6267 (54 FR 30009, July 18, 1989), are approved as
AMOCs for the corresponding requirements of this AD.
(v) Related Information
(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: (425) 917-6432; fax: (425) 917-6590; email:
bill.ashforth@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, 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.
(w) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 747-57A2331, dated November
12, 2009.
(ii) Boeing Service Bulletin 747-57-2244, Revision 1, dated July
28, 1988.
(3) 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.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 26, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-24412 Filed 10-4-12; 8:45 am]
BILLING CODE 4910-13-P
