Airworthiness Directives; The Boeing Company Model 747 Airplanes, 81430-81433 [2010-31985]
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Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations
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Alternative Methods of Compliance
(AMOCs)
(o)(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. Send information to Attn:
Nicholas Han, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle ACO, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6449; fax
(425) 917–6590. Information may be e-mailed
to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(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) or other
person 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 2006–05–09 are
approved as alternative methods of
compliance with the corresponding
requirements of this AD.
Material Incorporated by Reference
(p) You must use Boeing Alert Service
Bulletin 747–53A2499, dated August 11,
2005; or Boeing Service Bulletin 747–
53A2499, Revision 2, dated August 12, 2010;
as applicable; to do the actions required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Service Bulletin 747–53A2499,
Revision 2, dated August 12, 2010, under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Boeing Alert Service Bulletin
747–53A2499, dated August 11, 2005, on
April 13, 2006 (71 FR 12122, March 9, 2006).
(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; e-mail me.boecom@boeing.com;
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 also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
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information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
December 13, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–31992 Filed 12–27–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0674; Directorate
Identifier 2010–NM–012–AD; Amendment
39–16546; AD 2010–26–07]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD requires
repetitive inspections for cracking in the
body skin around the aft corners of the
nose wheel well; for certain airplanes,
repetitive inspections for cracking in the
skin splice plate at the aft corners of the
nose wheel well; and related
investigative and corrective actions if
necessary. This AD also requires
repetitive post-modification inspections
for cracking in the body skin and the
skin splice plate; for certain airplanes,
an inspection for steel cross-shaped
doublers on the larger aluminum
doublers; and corrective action if
necessary. This AD also requires
repetitive surface high frequency eddy
current (HFEC) inspections of a certain
bulkhead outer chord, skin splice plate,
and outer chord radius filler for
cracking; repetitive detailed inspections
for cracking of the bulkhead frame web
and body skin; and corrective actions if
necessary. This AD provides for
optional terminating action for certain
repetitive inspections. This AD was
prompted by reports of cracking of the
fuselage skin and adjacent internal skin
splice plate at the left and right nose
wheel well aft corners, and the outer
chord of the body station (BS) 400
bulkhead. We are issuing this AD to
detect and correct cracking of the
fuselage skin or splice plate, which,
together with cracking of the bulkhead
outer chord, could result in large skin
SUMMARY:
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cracks and subsequent in-flight rapid
decompression of the airplane.
DATES: This AD is effective February 1,
2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of February 1, 2011.
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; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this 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:
Steven Fox, Senior Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6425; fax (425) 917–6590; email: steven.fox@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to the
specified products. That NPRM
published in the Federal Register on
July 8, 2010 (75 FR 39189). That NPRM
proposed to require repetitive
inspections for cracking in the body
skin around the aft corners of the nose
wheel well; for certain airplanes,
repetitive inspections for cracking in the
skin splice plate at the aft corners of the
nose wheel well; and related
investigative and corrective actions if
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Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations
necessary. The NPRM also proposed to
require repetitive post-modification
inspections for cracking in the body
skin and the skin splice plate; for
certain airplanes, an inspection for steel
cross-shaped doublers on the larger
aluminum doublers; and corrective
action if necessary. The NPRM also
proposed to require repetitive surface
high frequency eddy current (HFEC)
inspections of a certain bulkhead outer
chord, skin splice plate, and outer chord
radius filler for cracking; repetitive
detailed inspections for cracking of the
bulkhead frame web and body skin; and
corrective actions if necessary. That
NPRM also proposed to provide for
optional terminating action for certain
repetitive inspections.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal and the FAA’s
response to each comment.
Request To Revise Paragraph (r) of the
NPRM
Boeing requested that we revise
paragraph (r) of the NPRM to note that
the threshold of the initial inspection, in
accordance with Boeing Document No.
D6–35022, Volumes 1 and 2
‘‘Supplemental Structural Inspection
Document (SSID) for Model 747
Airplanes,’’ Revision G, dated December
2000, Item F–4, remains as given in AD
2004–07–22 R1 (73 FR 1052, January 7,
2008) (A correction to AD 2004–07–22
R1 was published in the Federal
Register on February 14, 2008 (73 FR
8589)). Boeing stated that while the
inspection method and intervals
provided in Boeing Alert Service
Bulletin 747–53A2305, Revision 2,
dated January 15, 2009, are alternative
methods of compliance (AMOCs) to
Revision G of the Model 747 SSID, Item
F–4, the requirement to comply with the
SSID inspection threshold remains as
given in AD 2004–07–22 R1.
We disagree with the request to revise
paragraph (r) of this AD to include the
requested notation. Paragraph (r) of this
AD does not provide any indication of
change to the initial inspection
threshold for the initial inspection
according to Revision G of the Model
747 SSID, Item F–4. As the commenter
stated, the inspection threshold for Item
F–4 remains as given in AD 2004–07–
22 R1. Paragraph (b) of this AD also
indicates that no other AD is affected by
this AD. No change has been made to
the AD in this regard.
Request To Include Alternative
Inspection Procedures as AMOCs or To
Extend the Grace Period
Japan Airlines (JAL) requested
approval of an AMOC for inspections
for airplanes that have been previously
repaired. JAL stated that 14 of its Model
747–400 airplanes have had repair
doublers already installed in the
affected areas that deviate from Boeing
Alert Service Bulletin 747–53A2305,
Revision 2, dated January 15, 2009;
therefore, alternative inspection
procedures are necessary for the
repaired structure. JAL stated that it will
have to obtain AMOC approval for each
of its 14 airplanes. JAL also stated that
since it takes additional work for both
JAL and Boeing to obtain the AMOC
approval, an exception should be
allowed to admit all of the existing
repairs as an AMOC for the proposed
actions. JAL also proposed the
alternative of an approval letter from the
FAA for their existing repairs before the
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effective date of the AD. As an
alternative, JAL requested a grace period
to allow an extended compliance time
for the inspection of previously repaired
airplanes.
We disagree with the request for
AMOC approval for previously repaired
airplanes and for a grace period. An
AMOC cannot be included in an AD,
because an AMOC can be written for an
AD only after the AD is published.
Because the repairs previously done on
these 14 airplanes can be unique to each
airplane and are different from the
repair requirements of this AD, each
instance will need to be re-evaluated for
this AD as an AMOC to ensure
continued operational safety. However,
under the provisions of paragraph (u) of
this AD, after the AD is published we
will consider requests for approval of an
alternative method of compliance if
sufficient data are submitted to
substantiate that the previous repairs
would provide an acceptable level of
safety.
We also disagree with the request to
include a grace period. A grace period
of 1,500 flight hours from the effective
date of this AD was already included in
paragraphs (k), (o), and (r) of this AD.
No change has been made to 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
as proposed.
Costs of Compliance
We estimate that this AD affects 160
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
TABLE—ESTIMATED COSTS
Action
Inspections: Body Skin and
Skin Splice Plate.
Modification: Groups 1–3 1 .......
Modification: Groups 1–3 2 .......
Modification: Groups 4–8 3 .......
Modification: Groups 4–7 4 .......
Post-Mod LFEC Inspection 5 ....
Inspections: Bulkhead Outer
Chord 6.
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Average labor rate
per hour
Work hours
Cost per product
1
$85
$85
180
320
180
40
6
4
85
85
85
85
85
85
15,300
27,200
15,300
3,400
510
340
Number of U.S.-registered airplanes
Fleet cost
160 ..........................
$13,600.
Up
Up
Up
Up
Up
Up
Up
Up
Up
Up
Up
Up
to
to
to
to
to
to
27 ..................
27 ..................
133 ................
44 ..................
160 ................
160 ................
to
to
to
to
to
to
$413,100.
$734,400.
$2,034,900.
$149,600.
$81,600.
$54,400.
1 Installation of skin and splice plate doubler for Groups 1–3 airplanes that have not done Boeing Service Bulletin 747–53–2150 or Figure 35 of
Section 53–30–03 of the Boeing 747 Structural Repair Manual.
2 Installation of skin and splice plate doubler for Groups 1–3 airplanes that have done Boeing Service Bulletin 747–53–2150 or Figure 35 of
Section 53–30–03 of the Boeing 747 Structural Repair Manual.
3 Installation of skin and splice plate doubler for Groups 4–8 airplanes.
4 Installation of splice plate doubler for Groups 4–7 airplanes changed before Boeing Alert Service Bulletin 747–53A2305, Revision 2, dated
January 15, 2009.
5 Inspection for skin cracks around the fasteners at the periphery of the modification doublers.
6 Includes inspection of the frame web and body skin.
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Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations
Authority for this Rulemaking
§ 39.13
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
■
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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:
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■
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.
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[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
2010–26–07 The Boeing Company:
Amendment 39–16546; Docket No.
FAA–2010–0674; Directorate Identifier
2010–NM–012–AD.
Effective Date
(a) This AD is effective February 1, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all 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.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Unsafe Condition
(e) This AD results from reports of cracking
of the fuselage skin and adjacent internal
skin splice plate at the left and right nose
wheel well aft corners, and the outer chord
of the body station (BS) 400 bulkhead. The
Federal Aviation Administration is issuing
this AD to detect and correct cracking of the
fuselage skin or splice plate, which, together
with cracking of the bulkhead outer chord,
could result in large skin cracks and
subsequent in-flight rapid decompression of
the airplane.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Pre-Modification Inspections
(g) For airplanes in Groups 1 through 3, as
identified in Boeing Alert Service Bulletin
747–53A2305, Revision 2, dated January 15,
2009, that have not been modified in
accordance with Boeing Service Bulletin
747–53–2150; have not been repaired in
accordance with Figure 35 of Section 53–30–
03 of Boeing 747 Structural Repair Manual
(SRM); and have not been modified in
accordance with Boeing Alert Service
Bulletin 747–53A2305: Before the
accumulation of 3,000 total flight cycles, or
within 1,500 flight cycles after the effective
date of this AD, whichever occurs later, do
an external detailed inspection for cracks in
the body skin around the aft corners of the
nose wheel well, and skin splice plate at the
aft corners of the nose wheel well, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2305, Revision 2, dated January 15,
2009.
(h) For airplanes in Groups 1 through 3, as
identified in Boeing Alert Service Bulletin
747–53A2305, Revision 2, dated January 15,
2009, that have been modified in accordance
with Boeing Service Bulletin 747–53–2150;
or repaired in accordance with Figure 35 of
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Section 53–30–03 of Boeing 747 SRM: Within
6,000 flight cycles after doing the
modification or repair, or within 1,500 flight
cycles after the effective date of this AD,
whichever occurs later, do an external
detailed inspection for cracks in the body
skin around the aft corners of the nose wheel
well, and skin splice plate at the aft corners
of the nose wheel well, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–53A2305,
Revision 2, dated January 15, 2009.
(i) For airplanes in Groups 4 through 7, as
identified in Boeing Alert Service Bulletin
747–53A2305, Revision 2, dated January 15,
2009, that have not been modified in
accordance with Boeing Alert Service
Bulletin 747–53A2305: Prior to the
accumulation of 3,000 total flight cycles, or
within 1,500 flight cycles after the effective
date of this AD, whichever occurs later, do
an external detailed inspection for cracks in
the body skin around the aft corners of the
nose wheel well, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2305, Revision 2,
dated January 15, 2009.
(j) For airplanes in Groups 4 through 7, as
identified in Boeing Alert Service Bulletin
747–53A2305, Revision 2, dated January 15,
2009, that have been modified in accordance
with Boeing Service Bulletin 747–53–2305,
dated June 27, 1991; or Revision 1, dated
May 22, 1997: Within 1,000 flight cycles after
the effective date of this AD, do a one-time
external general visual inspection for steel
cross-shaped doublers, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–53A2305,
Revision 2, dated January 15, 2009. If no
cross-shaped doublers are installed, within
1,500 flight cycles after the effective date of
this AD, install cross-shaped doublers, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2305, Revision 2, dated January 15,
2009.
(k) For airplanes in Group 8, as identified
in Boeing Alert Service Bulletin 747–
53A2305, Revision 2, dated January 15, 2009:
Prior to the accumulation of 3,000 total flight
cycles, or within 1,500 flight cycles after the
effective date of this AD, whichever occurs
later, do an external detailed inspection for
cracks in the body skin around the aft corners
of the nose wheel well, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–53A2305,
Revision 2, dated January 15, 2009.
(l) If no crack is found during any
inspection required by paragraph (g), (h), (i),
or (k) of this AD, repeat the applicable
inspection specified in paragraph (g), (h), (i),
or (k) of this AD thereafter at intervals not to
exceed 1,500 flight cycles, until the
modification specified in paragraph (n) of
this AD is accomplished.
(m) If any crack is found during any
inspection required by paragraph (g), (h), (i),
(k), or (l) of this AD, before further flight,
modify the aft corners of the nose wheel well
by installing modification doublers and
doing all applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2305, Revision 2,
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dated January 15, 2009, except as required by
paragraph (t) of this AD.
Optional Terminating Action
(n) Modification of the aft corners of the
nose wheel well by installing modification
doublers and doing all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2305, Revision 2, dated January 15,
2009, terminates the repetitive inspections
required by paragraph (l) of this AD for the
modified side only. Where Boeing Alert
Service Bulletin 747–53A2305, Revision 2,
dated January 15, 2009, specifies to contact
Boeing for appropriate action, repair using a
method approved in accordance with the
procedures specified in paragraph (u) of this
AD.
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Post-Modification Repetitive Inspections
(o) For airplanes on which the
modification specified in Boeing Alert
Service Bulletin 747–53A2305, Revision 2,
dated January 15, 2009, has been done: At the
applicable time specified in paragraph (o)(1)
or (o)(2) of this AD, do an external low
frequency eddy current inspection for skin
cracks around the fasteners at the periphery
of the modification doublers, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2305,
Revision 2, dated January 15, 2009.
(1) For airplanes on which the edge row
fastener holes common to the external
modification doublers have been zero-timed
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2305, Revision 2, dated January 15,
2009: Within 15,000 flight cycles after
accomplishing the modification, or within
1,500 flight cycles after the effective date of
this AD, whichever occurs later.
(2) For airplanes on which the edge row
fastener holes common to the external
modification doublers have not been zerotimed in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2305, Revision 2,
dated January 15, 2009: Prior to the
accumulation of 15,000 total flight cycles, or
within 1,500 flight cycles after the effective
date of this AD, whichever occurs later.
(p) If no cracking is found during the
inspection required by paragraph (o) of this
AD, repeat the inspection specified in
paragraph (o) of this AD thereafter at
intervals not to exceed 1,500 flight cycles.
(q) If any cracking is found during any
inspection required by paragraph (o) or (p) of
this AD, before further flight, repair using a
method approved in accordance with the
procedures specified in paragraph (u) of this
AD.
Body Station (BS) 400 Bulkhead Outer
Chord Inspection
(r) For all airplanes: At the latest of the
times specified in paragraphs (r)(1), (r)(2),
and (r)(3) of this AD, do a surface HFEC
inspection for cracking in the BS 400
bulkhead outer chord, skin splice plate, and
outer chord radius filler; and a detailed
inspection for cracking of the bulkhead frame
web and body skin; in accordance with the
Accomplishment Instructions of Boeing Alert
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Service Bulletin 747–53A2305, Revision 2,
dated January 15, 2009. If no cracking is
found during any inspection, repeat the
inspection one time within 6,000 flight
cycles, and thereafter at intervals not to
exceed 3,000 flight cycles.
(1) Before the accumulation of 20,000 total
flight cycles.
(2) Within 3,000 flight cycles after doing
the HFEC inspection required by AD 2004–
07–22 R1, Amendment 39–15326, for
structural significant item (SSI) F–4B of the
Boeing Document No. D6–35022,
‘‘Supplemental Structural Inspection
Document (SSID) for Model 747 Airplanes,’’
Revision G, dated December 2000.
(3) Within 1,500 flight cycles after the
effective date of this AD.
(s) If any cracking is found during any
inspection required by paragraph (r) of this
AD, before further flight, repair in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2305,
Revision 2, dated January 15, 2009, except as
required by paragraph (t) of this AD. Within
6,000 flight cycles after doing the repair, do
the inspections specified in paragraph (r) of
this AD, and repeat the inspections thereafter
at intervals not to exceed 3,000 flight cycles.
Service Bulletin Exception
(t) If any cracking is found during any
inspection required by this AD, and Boeing
Alert Service Bulletin 747–53A2305,
Revision 2, dated January 15, 2009, 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 (u) of this
AD.
Alternative Methods of Compliance
(AMOCs)
(u)(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. Send information to Attn: Steven
Fox, Senior Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6425; fax (425) 917–6590.
Information may be e-mailed to: 9–ANM–
Seattle-ACO–AMOC–Requests@faa.gov.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(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.
PO 00000
Frm 00063
Fmt 4700
Sfmt 4700
81433
Related Information
(v) For more information about this AD,
contact Steven Fox, Senior Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6425; fax
(425) 917–6590; e-mail: steven.fox@faa.gov.
Material Incorporated by Reference
(w) You must use Boeing Alert Service
Bulletin 747–53A2305, Revision 2, dated
January 15, 2009, to do the actions required
by this AD, unless the AD specifies
otherwise. The optional actions, if
accomplished, shall be done in accordance
with Boeing Alert Service Bulletin 747–
53A2305, Revision 2, dated January 15, 2009.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(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; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(3) 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.
(4) 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 an NARA facility, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
December 13, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–31985 Filed 12–27–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1201; Directorate
Identifier 2010–NM–081–AD; Amendment
39–16551; AD 2010–26–12]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A321–211, –212, –231, and –232
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
E:\FR\FM\28DER1.SGM
28DER1
]]>Agencies
[Federal Register Volume 75, Number 248 (Tuesday, December 28, 2010)]
[Rules and Regulations]
[Pages 81430-81433]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-31985]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0674; Directorate Identifier 2010-NM-012-AD;
Amendment 39-16546; AD 2010-26-07]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD requires repetitive inspections for
cracking in the body skin around the aft corners of the nose wheel
well; for certain airplanes, repetitive inspections for cracking in the
skin splice plate at the aft corners of the nose wheel well; and
related investigative and corrective actions if necessary. This AD also
requires repetitive post-modification inspections for cracking in the
body skin and the skin splice plate; for certain airplanes, an
inspection for steel cross-shaped doublers on the larger aluminum
doublers; and corrective action if necessary. This AD also requires
repetitive surface high frequency eddy current (HFEC) inspections of a
certain bulkhead outer chord, skin splice plate, and outer chord radius
filler for cracking; repetitive detailed inspections for cracking of
the bulkhead frame web and body skin; and corrective actions if
necessary. This AD provides for optional terminating action for certain
repetitive inspections. This AD was prompted by reports of cracking of
the fuselage skin and adjacent internal skin splice plate at the left
and right nose wheel well aft corners, and the outer chord of the body
station (BS) 400 bulkhead. We are issuing this AD to detect and correct
cracking of the fuselage skin or splice plate, which, together with
cracking of the bulkhead outer chord, could result in large skin cracks
and subsequent in-flight rapid decompression of the airplane.
DATES: This AD is effective February 1, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of February 1,
2011.
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; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this 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: Steven Fox, Senior Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6425; fax (425) 917-6590; e-mail: steven.fox@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness directive (AD) that would apply to
the specified products. That NPRM published in the Federal Register on
July 8, 2010 (75 FR 39189). That NPRM proposed to require repetitive
inspections for cracking in the body skin around the aft corners of the
nose wheel well; for certain airplanes, repetitive inspections for
cracking in the skin splice plate at the aft corners of the nose wheel
well; and related investigative and corrective actions if
[[Page 81431]]
necessary. The NPRM also proposed to require repetitive post-
modification inspections for cracking in the body skin and the skin
splice plate; for certain airplanes, an inspection for steel cross-
shaped doublers on the larger aluminum doublers; and corrective action
if necessary. The NPRM also proposed to require repetitive surface high
frequency eddy current (HFEC) inspections of a certain bulkhead outer
chord, skin splice plate, and outer chord radius filler for cracking;
repetitive detailed inspections for cracking of the bulkhead frame web
and body skin; and corrective actions if necessary. That NPRM also
proposed to provide for optional terminating action for certain
repetitive inspections.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.
Request To Revise Paragraph (r) of the NPRM
Boeing requested that we revise paragraph (r) of the NPRM to note
that the threshold of the initial inspection, in accordance with Boeing
Document No. D6-35022, Volumes 1 and 2 ``Supplemental Structural
Inspection Document (SSID) for Model 747 Airplanes,'' Revision G, dated
December 2000, Item F-4, remains as given in AD 2004-07-22 R1 (73 FR
1052, January 7, 2008) (A correction to AD 2004-07-22 R1 was published
in the Federal Register on February 14, 2008 (73 FR 8589)). Boeing
stated that while the inspection method and intervals provided in
Boeing Alert Service Bulletin 747-53A2305, Revision 2, dated January
15, 2009, are alternative methods of compliance (AMOCs) to Revision G
of the Model 747 SSID, Item F-4, the requirement to comply with the
SSID inspection threshold remains as given in AD 2004-07-22 R1.
We disagree with the request to revise paragraph (r) of this AD to
include the requested notation. Paragraph (r) of this AD does not
provide any indication of change to the initial inspection threshold
for the initial inspection according to Revision G of the Model 747
SSID, Item F-4. As the commenter stated, the inspection threshold for
Item F-4 remains as given in AD 2004-07-22 R1. Paragraph (b) of this AD
also indicates that no other AD is affected by this AD. No change has
been made to the AD in this regard.
Request To Include Alternative Inspection Procedures as AMOCs or To
Extend the Grace Period
Japan Airlines (JAL) requested approval of an AMOC for inspections
for airplanes that have been previously repaired. JAL stated that 14 of
its Model 747-400 airplanes have had repair doublers already installed
in the affected areas that deviate from Boeing Alert Service Bulletin
747-53A2305, Revision 2, dated January 15, 2009; therefore, alternative
inspection procedures are necessary for the repaired structure. JAL
stated that it will have to obtain AMOC approval for each of its 14
airplanes. JAL also stated that since it takes additional work for both
JAL and Boeing to obtain the AMOC approval, an exception should be
allowed to admit all of the existing repairs as an AMOC for the
proposed actions. JAL also proposed the alternative of an approval
letter from the FAA for their existing repairs before the effective
date of the AD. As an alternative, JAL requested a grace period to
allow an extended compliance time for the inspection of previously
repaired airplanes.
We disagree with the request for AMOC approval for previously
repaired airplanes and for a grace period. An AMOC cannot be included
in an AD, because an AMOC can be written for an AD only after the AD is
published. Because the repairs previously done on these 14 airplanes
can be unique to each airplane and are different from the repair
requirements of this AD, each instance will need to be re-evaluated for
this AD as an AMOC to ensure continued operational safety. However,
under the provisions of paragraph (u) of this AD, after the AD is
published we will consider requests for approval of an alternative
method of compliance if sufficient data are submitted to substantiate
that the previous repairs would provide an acceptable level of safety.
We also disagree with the request to include a grace period. A
grace period of 1,500 flight hours from the effective date of this AD
was already included in paragraphs (k), (o), and (r) of this AD.
No change has been made to 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 as proposed.
Costs of Compliance
We estimate that this AD affects 160 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Table--Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average labor rate Number of U.S.-registered
Action Work hours per hour Cost per product airplanes Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections: Body Skin and Skin Splice 1 $85 $85 160...................... $13,600.
Plate.
Modification: Groups 1-3 \1\.......... 180 85 15,300 Up to 27................. Up to $413,100.
Modification: Groups 1-3 \2\.......... 320 85 27,200 Up to 27................. Up to $734,400.
Modification: Groups 4-8 \3\.......... 180 85 15,300 Up to 133................ Up to $2,034,900.
Modification: Groups 4-7 \4\.......... 40 85 3,400 Up to 44................. Up to $149,600.
Post-Mod LFEC Inspection \5\.......... 6 85 510 Up to 160................ Up to $81,600.
Inspections: Bulkhead Outer Chord \6\. 4 85 340 Up to 160................ Up to $54,400.
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ Installation of skin and splice plate doubler for Groups 1-3 airplanes that have not done Boeing Service Bulletin 747-53-2150 or Figure 35 of
Section 53-30-03 of the Boeing 747 Structural Repair Manual.
\2\ Installation of skin and splice plate doubler for Groups 1-3 airplanes that have done Boeing Service Bulletin 747-53-2150 or Figure 35 of Section 53-
30-03 of the Boeing 747 Structural Repair Manual.
\3\ Installation of skin and splice plate doubler for Groups 4-8 airplanes.
\4\ Installation of splice plate doubler for Groups 4-7 airplanes changed before Boeing Alert Service Bulletin 747-53A2305, Revision 2, dated January
15, 2009.
\5\ Inspection for skin cracks around the fasteners at the periphery of the modification doublers.
\6\ Includes inspection of the frame web and body skin.
[[Page 81432]]
Authority for this Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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 adding the following new airworthiness
directive (AD):
2010-26-07 The Boeing Company: Amendment 39-16546; Docket No. FAA-
2010-0674; Directorate Identifier 2010-NM-012-AD.
Effective Date
(a) This AD is effective February 1, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all 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.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from reports of cracking of the fuselage
skin and adjacent internal skin splice plate at the left and right
nose wheel well aft corners, and the outer chord of the body station
(BS) 400 bulkhead. The Federal Aviation Administration is issuing
this AD to detect and correct cracking of the fuselage skin or
splice plate, which, together with cracking of the bulkhead outer
chord, could result in large skin cracks and subsequent in-flight
rapid decompression of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Pre-Modification Inspections
(g) For airplanes in Groups 1 through 3, as identified in Boeing
Alert Service Bulletin 747-53A2305, Revision 2, dated January 15,
2009, that have not been modified in accordance with Boeing Service
Bulletin 747-53-2150; have not been repaired in accordance with
Figure 35 of Section 53-30-03 of Boeing 747 Structural Repair Manual
(SRM); and have not been modified in accordance with Boeing Alert
Service Bulletin 747-53A2305: Before the accumulation of 3,000 total
flight cycles, or within 1,500 flight cycles after the effective
date of this AD, whichever occurs later, do an external detailed
inspection for cracks in the body skin around the aft corners of the
nose wheel well, and skin splice plate at the aft corners of the
nose wheel well, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-53A2305, Revision 2, dated
January 15, 2009.
(h) For airplanes in Groups 1 through 3, as identified in Boeing
Alert Service Bulletin 747-53A2305, Revision 2, dated January 15,
2009, that have been modified in accordance with Boeing Service
Bulletin 747-53-2150; or repaired in accordance with Figure 35 of
Section 53-30-03 of Boeing 747 SRM: Within 6,000 flight cycles after
doing the modification or repair, or within 1,500 flight cycles
after the effective date of this AD, whichever occurs later, do an
external detailed inspection for cracks in the body skin around the
aft corners of the nose wheel well, and skin splice plate at the aft
corners of the nose wheel well, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2305, Revision 2, dated January 15, 2009.
(i) For airplanes in Groups 4 through 7, as identified in Boeing
Alert Service Bulletin 747-53A2305, Revision 2, dated January 15,
2009, that have not been modified in accordance with Boeing Alert
Service Bulletin 747-53A2305: Prior to the accumulation of 3,000
total flight cycles, or within 1,500 flight cycles after the
effective date of this AD, whichever occurs later, do an external
detailed inspection for cracks in the body skin around the aft
corners of the nose wheel well, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2305, Revision 2, dated January 15, 2009.
(j) For airplanes in Groups 4 through 7, as identified in Boeing
Alert Service Bulletin 747-53A2305, Revision 2, dated January 15,
2009, that have been modified in accordance with Boeing Service
Bulletin 747-53-2305, dated June 27, 1991; or Revision 1, dated May
22, 1997: Within 1,000 flight cycles after the effective date of
this AD, do a one-time external general visual inspection for steel
cross-shaped doublers, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2305, Revision
2, dated January 15, 2009. If no cross-shaped doublers are
installed, within 1,500 flight cycles after the effective date of
this AD, install cross-shaped doublers, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2305, Revision 2, dated January 15, 2009.
(k) For airplanes in Group 8, as identified in Boeing Alert
Service Bulletin 747-53A2305, Revision 2, dated January 15, 2009:
Prior to the accumulation of 3,000 total flight cycles, or within
1,500 flight cycles after the effective date of this AD, whichever
occurs later, do an external detailed inspection for cracks in the
body skin around the aft corners of the nose wheel well, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2305, Revision 2, dated January 15, 2009.
(l) If no crack is found during any inspection required by
paragraph (g), (h), (i), or (k) of this AD, repeat the applicable
inspection specified in paragraph (g), (h), (i), or (k) of this AD
thereafter at intervals not to exceed 1,500 flight cycles, until the
modification specified in paragraph (n) of this AD is accomplished.
(m) If any crack is found during any inspection required by
paragraph (g), (h), (i), (k), or (l) of this AD, before further
flight, modify the aft corners of the nose wheel well by installing
modification doublers and doing all applicable related investigative
and corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2305, Revision
2,
[[Page 81433]]
dated January 15, 2009, except as required by paragraph (t) of this
AD.
Optional Terminating Action
(n) Modification of the aft corners of the nose wheel well by
installing modification doublers and doing all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2305, Revision 2, dated January 15, 2009, terminates the
repetitive inspections required by paragraph (l) of this AD for the
modified side only. Where Boeing Alert Service Bulletin 747-53A2305,
Revision 2, dated January 15, 2009, specifies to contact Boeing for
appropriate action, repair using a method approved in accordance
with the procedures specified in paragraph (u) of this AD.
Post-Modification Repetitive Inspections
(o) For airplanes on which the modification specified in Boeing
Alert Service Bulletin 747-53A2305, Revision 2, dated January 15,
2009, has been done: At the applicable time specified in paragraph
(o)(1) or (o)(2) of this AD, do an external low frequency eddy
current inspection for skin cracks around the fasteners at the
periphery of the modification doublers, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2305, Revision 2, dated January 15, 2009.
(1) For airplanes on which the edge row fastener holes common to
the external modification doublers have been zero-timed in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2305, Revision 2, dated January 15, 2009:
Within 15,000 flight cycles after accomplishing the modification, or
within 1,500 flight cycles after the effective date of this AD,
whichever occurs later.
(2) For airplanes on which the edge row fastener holes common to
the external modification doublers have not been zero-timed in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2305, Revision 2, dated January 15, 2009:
Prior to the accumulation of 15,000 total flight cycles, or within
1,500 flight cycles after the effective date of this AD, whichever
occurs later.
(p) If no cracking is found during the inspection required by
paragraph (o) of this AD, repeat the inspection specified in
paragraph (o) of this AD thereafter at intervals not to exceed 1,500
flight cycles.
(q) If any cracking is found during any inspection required by
paragraph (o) or (p) of this AD, before further flight, repair using
a method approved in accordance with the procedures specified in
paragraph (u) of this AD.
Body Station (BS) 400 Bulkhead Outer Chord Inspection
(r) For all airplanes: At the latest of the times specified in
paragraphs (r)(1), (r)(2), and (r)(3) of this AD, do a surface HFEC
inspection for cracking in the BS 400 bulkhead outer chord, skin
splice plate, and outer chord radius filler; and a detailed
inspection for cracking of the bulkhead frame web and body skin; in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2305, Revision 2, dated January 15, 2009. If
no cracking is found during any inspection, repeat the inspection
one time within 6,000 flight cycles, and thereafter at intervals not
to exceed 3,000 flight cycles.
(1) Before the accumulation of 20,000 total flight cycles.
(2) Within 3,000 flight cycles after doing the HFEC inspection
required by AD 2004-07-22 R1, Amendment 39-15326, for structural
significant item (SSI) F-4B of the Boeing Document No. D6-35022,
``Supplemental Structural Inspection Document (SSID) for Model 747
Airplanes,'' Revision G, dated December 2000.
(3) Within 1,500 flight cycles after the effective date of this
AD.
(s) If any cracking is found during any inspection required by
paragraph (r) of this AD, before further flight, repair in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2305, Revision 2, dated January 15, 2009,
except as required by paragraph (t) of this AD. Within 6,000 flight
cycles after doing the repair, do the inspections specified in
paragraph (r) of this AD, and repeat the inspections thereafter at
intervals not to exceed 3,000 flight cycles.
Service Bulletin Exception
(t) If any cracking is found during any inspection required by
this AD, and Boeing Alert Service Bulletin 747-53A2305, Revision 2,
dated January 15, 2009, 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
(u) of this AD.
Alternative Methods of Compliance (AMOCs)
(u)(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. Send information to
Attn: Steven Fox, Senior Aerospace Engineer, Airframe Branch, ANM-
120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue
SW., Renton, Washington 98057-3356; telephone (425) 917-6425; fax
(425) 917-6590. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(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.
Related Information
(v) For more information about this AD, contact Steven Fox,
Senior Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6425; fax (425) 917-6590;
e-mail: steven.fox@faa.gov.
Material Incorporated by Reference
(w) You must use Boeing Alert Service Bulletin 747-53A2305,
Revision 2, dated January 15, 2009, to do the actions required by
this AD, unless the AD specifies otherwise. The optional actions, if
accomplished, shall be done in accordance with Boeing Alert Service
Bulletin 747-53A2305, Revision 2, dated January 15, 2009.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(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; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(3) 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.
(4) 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 an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on December 13, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-31985 Filed 12-27-10; 8:45 am]
BILLING CODE 4910-13-P
