[Federal Register: August 13, 2008 (Volume 73, Number 157)]
[Rules and Regulations]
[Page 47035-47039]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13au08-4]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0043; Directorate Identifier 2007-NM-058-AD;
Amendment 39-15632; AD 2008-16-14]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and
747SP Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 747 series airplanes. That
AD currently requires inspecting to detect cracking in certain lower
lobe fuselage skin lap joints, doing repetitive inspections for
cracking at certain fastener locations having countersunk fasteners,
and replacing countersunk fasteners with protruding head fasteners at
certain fastener locations. This new AD requires replacing a previous
high-frequency eddy current (HFEC) inspection method with a new HFEC
inspection method, adding a one-time inspection for cracking of certain
airplanes, and terminating the adjustment factor for the inspection
compliance times based on cabin differential pressure. This AD also
requires inspecting additional lap joints. This AD results from reports
of fuselage skin cracks found at certain countersunk fastener locations
in the upper row of lap joints near the wing-to-body fairings, and from
a report that the presence of Alodine-coated rivets could cause faulty
results during the required inspections using the optional sliding
probe HFEC inspection method specified in the existing AD. We are
issuing this AD to prevent reduced structural integrity of the
fuselage.
DATES: This AD becomes effective September 17, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of September 17,
2008.
On August 24, 1994 (59 FR 37659, July 25, 1994), the Director of
the Federal Register approved the incorporation by reference of Boeing
Service Bulletin 747-53A2312, including the ``Addendum,'' Revision 2,
dated October 8, 1992.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
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 (telephone 800-647-5527) is the 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: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an AD that supersedes AD 94-15-06,
amendment 39-8977 (59 FR 37659, July 25, 1994). The existing AD applies
to certain Boeing Model 747 series airplanes. That supplemental NPRM
was published in the Federal Register on May 7, 2008 (73 FR 25601).
That supplemental NPRM proposed to continue to require inspecting to
detect cracking in certain lower lobe fuselage skin lap joints, doing
repetitive
[[Page 47036]]
inspections for cracking at certain fastener locations having
countersunk fasteners, and replacing countersunk fasteners with
protruding head fasteners at certain fastener locations. That
supplemental NPRM also proposed to require replacing a previous high-
frequency eddy current (HFEC) inspection method with a new HFEC
inspection method, adding a one-time inspection for cracking of certain
airplanes, and terminating the adjustment factor for the inspection
compliance times based on cabin differential pressure. That
supplemental NPRM also proposed to require inspecting additional lap
joints.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the single comment that has
been received on the supplemental NPRM. The commenter, Boeing, supports
the NPRM.
Conclusion
We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD as proposed.
Costs of Compliance
There are about 348 airplanes in the worldwide fleet. We estimate
that this AD affects 90 airplanes of U.S. registry. The issue
associated with Alodine-coated aluminum rivets occurs on 162 airplanes
in the worldwide fleet and affects 24 airplanes of U.S. registry. The
following table provides the estimated costs for U.S. operators to
comply with this AD. The average labor rate is $80 per work hour.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Action Work hours Parts affected Cost per Fleet cost
airplanes airplane
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD 14 $0 90 $1,120, per $100,800, per
94-15-06 and retained in inspection inspection
this AD). cycle. cycle.
Inspections (required by AD 82 0 90 $6,560, per $590,400, per
94-15-06 and retained in inspection inspection
this AD). cycle. cycle.
Modification (required by AD 124 (\1\) 90 $9,920.......... $892,800.
94-15-06 and retained in
this AD).
One-time inspection (new 4 0 24 $320............ $7,680.
action).
----------------------------------------------------------------------------------------------------------------
\1\ Minimal.
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); and
(3) 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-8977 (59 FR 37659, July 25, 1994) and by adding
the following new airworthiness directive (AD):
2008-16-14 Boeing: Amendment 39-15632. Docket No. FAA-2007-0043;
Directorate Identifier 2007-NM-058-AD.
Effective Date
(a) This AD becomes effective September 17, 2008.
Affected ADs
(b) This AD supersedes AD 94-15-06.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and
747SP series airplanes, certificated in any category, as identified
in Boeing Alert Service Bulletin 747-53A2312, Revision 3, dated
February 8, 2007.
[[Page 47037]]
Unsafe Condition
(d) This AD results from reports of fuselage skin cracks found
at certain countersunk fastener locations in the upper row of lap
joints near the wing-to-body fairings, and from a report that the
presence of Alodine-coated rivets could cause faulty results during
the required inspections using the optional sliding probe high
frequency eddy current (HFEC) inspection method specified in AD 94-
15-06. We are issuing this AD to prevent reduced structural
integrity of the fuselage.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Requirements of AD 94-15-06 With Revised Body Station and Stringer
Locations
Inspections for Airplanes Having Line Numbers 201 Through 765 Inclusive
(f) For airplanes having line numbers 201 through 765 inclusive:
Conduct an HFEC inspection to detect cracking of the lower lobe lap
joints in the vicinity of the wing-to-body fairings, in accordance
with Boeing Alert Service Bulletin 747-53A2312, dated June 12, 1989;
Revision 1, dated March 29, 1990; Revision 2, dated October 8, 1992;
or Revision 3, dated February 8, 2007; except as provided by
paragraph (u) of this AD; at the time specified in paragraph (f)(1),
(f)(2), (f)(3), or (f)(4) of this AD, as applicable. As of the
effective date of this AD, only Revision 3 shall be used. Repeat
this inspection thereafter at intervals not to exceed 4,000 landings
until the inspection required by paragraph (j) of this AD is
accomplished.
(1) For airplanes that have accumulated less than 11,200 total
landings as of February 5, 1990 (the effective date of AD 90-01-07,
amendment 39-6440, which was superseded by AD 94-15-06): Prior to
the accumulation of 11,000 total landings, or within the next 1,000
landings after February 5, 1990, whichever occurs later.
(2) For airplanes that have accumulated 11,200 or more total
landings but less than 15,201 total landings as of February 5, 1990:
Within the next 1,000 landings after February 5, 1990, or prior to
the accumulation of 15,500 total landings, whichever occurs earlier.
(3) For airplanes that have accumulated 15,201 or more total
landings but less than 18,200 total landings as of February 5, 1990:
Within the next 300 landings after February 5, 1990, or prior to the
accumulation of 18,250 total landings, whichever occurs earlier.
(4) For airplanes that have accumulated 18,200 or more landings
as of February 5, 1990: Within the next 50 landings after February
5, 1990.
Repair and Modification for Airplanes Having Line Numbers 201 Through
765 Inclusive
(g) For airplanes having line numbers 201 through 765 inclusive:
Accomplish the requirements of paragraphs (g)(1) and (g)(2) of this
AD.
(1) If any cracking is detected during the inspections required
by paragraph (f) of this AD, prior to further flight, repair in
accordance with Boeing Alert Service Bulletin 747-53A2312, dated
June 12, 1989; Revision 1, dated March 29, 1990; Revision 2, dated
October 8, 1992; or Revision 3, dated February 8, 2007; except as
provided by paragraph (u) of this AD. As of the effective date of
this AD, only Revision 3 shall be used.
(2) Prior to the accumulation of 20,000 total landings, or
within the next 3,000 landings after February 5, 1990 (the effective
date of AD 90-01-07), whichever occurs later, modify the airplane by
replacing countersunk fasteners in the upper row of the lower lobe
lap joints in the vicinity of the wing-to-body fairings with
protruding head fasteners, in accordance with the procedures
described in Boeing Alert Service Bulletin 747-53A2312, dated June
12, 1989; Revision 1, dated March 29, 1990; Revision 2, dated
October 8, 1992; or Revision 3, dated February 8, 2007; except as
provided by paragraph (u) of this AD. As of the effective date of
this AD, only Revision 3 shall be used.
Adjustments for Cabin Differential Pressure for Airplanes Having Line
Numbers 201 Through 765 Inclusive
(h) For airplanes having line numbers 201 through 765 inclusive:
Before the effective date of this AD, for purposes of complying with
paragraphs (f) and (g) of this AD, the number of landings may be
determined to equal the number of pressurization cycles where the
cabin pressure differential was greater than 2.0 psi.
(i) For airplanes having line numbers 201 through 765 inclusive:
Before the effective date of this AD, for Model 747SR series
airplanes only, based on continued mixed operation of lower cabin
differentials, the inspection and modification compliance times
specified in paragraphs (f) and (g) of this AD may be multiplied by
a 1.2 adjustment factor.
General Visual Inspection for Countersunk Fasteners for All Airplanes
(j) For all airplanes: Prior to the accumulation of 11,000 total
landings, or within 1,000 landings after August 24, 1994 (the
effective date of AD 94-15-06), whichever occurs later, conduct a
general visual inspection, unless previously accomplished within the
last 3,000 landings prior to August 24, 1994, to determine if
countersunk fasteners have been installed in the lap joints listed
in paragraph (j)(1) or (j)(2) of this AD, as applicable, in
accordance with the procedures described in Boeing Service Bulletin
747-53A2312, Revision 2, dated October 8, 1992; or Revision 3, dated
February 8, 2007; except as provided by paragraph (u) of this AD. As
of the effective date of this AD, only Revision 3 shall be used.
Accomplishment of this inspection terminates the inspection
requirements of paragraph (f) of this AD.
(1) For Model 747-100, -200, -300, -400, and 747SR series
airplanes: From body stations (BS) 741 to 1000 at stringers (S)-34L,
S-34R, S-39L, S-39R, S-44L, and S-44R, and from BS 1480 to 1741 at
S-34L, S-34R, S-40L, and S-40R.
(2) For Model 747SP series airplanes: From BS 560 to 800 at S-
34L, S-34R, S-39L, S-39R, S-44L, and S-44R, and from BS 1640 to 1741
at S-34L, S-34R, S-40L, and S-40R.
Corrective Action for Countersunk Fasteners for All Airplanes
(k) For all airplanes: If no countersunk fastener is found in
the upper row of a lap joint during the inspection required by
paragraph (j) of this AD, no further action is required by this AD
for that lap joint.
(l) For all airplanes: If any countersunk fastener is found in
the upper row of a lap joint during the inspection required by
paragraph (j) of this AD, prior to further flight, perform an HFEC
inspection to detect cracking at all fastener locations in the lap
joint where a countersunk fastener was found during the inspection
required by paragraph (j) of this AD, in accordance with the
procedures described in Boeing Service Bulletin 747-53A2312,
Revision 2, dated October 8, 1992; or Revision 3, dated February 8,
2007; except as provided by paragraph (u) of this AD. As of the
effective date of this AD, only Revision 3 shall be used.
Repetitive Inspections
(m) If no cracking is detected during any inspection required by
paragraphs (l) and (q) of this AD, at any fastener location where a
countersunk fastener was found during the inspection required by
paragraph (j) or (q)(1) of this AD, repeat the HFEC inspection
thereafter at intervals not to exceed 4,000 landings, in accordance
with the procedures described in Boeing Service Bulletin 747-
53A2312, Revision 2, dated October 8, 1992; or Revision 3, dated
February 8, 2007; except as provided by paragraph (u) of this AD. As
of the effective date of this AD, only Revision 3 shall be used. As
an alternative to the HFEC inspection, operators may perform a
detailed inspection to detect cracking at any fastener location
where a countersunk fastener was found, in accordance with the
procedures described in Boeing Service Alert Bulletin 747-53A2312,
Revision 3, dated February 8, 2007; except as provided by paragraph
(u) of this AD. Perform the detailed inspection within the next
4,000 landings after the HFEC inspection required by paragraph (l)
of this AD, and repeat the inspection thereafter at intervals not to
exceed 500 landings. At any of the subsequent inspection cycles,
operators may use either inspection method provided that the
corresponding inspection interval is used to determine the
compliance time of the next inspection.
(n) If cracking is detected during any inspection required by
paragraph (l), (m), (p), or (q) of this AD, at any fastener location
where a countersunk fastener was found during the inspection
required by paragraph (j) or (q)(1) of this AD, prior to further
flight, repair and modify that lap joint in accordance with Boeing
Service Bulletin 747-53A2312, Revision 2, dated October 8, 1992; or
Revision 3, dated February 8, 2007; except as provided by paragraph
(u) of this AD. As of the effective date of this AD, only Revision 3
shall be used. Accomplishment of
[[Page 47038]]
this repair and modification terminates the repetitive inspections
required by paragraph (m) of this AD for that lap joint.
Modification of Countersunk Fasteners for All Airplanes
(o) For all airplanes: Prior to the accumulation of 20,000 total
landings or within 1,000 landings after August 24, 1994, whichever
occurs later, modify all fastener locations where a countersunk
fastener was found during the inspections required by paragraph (j)
of this AD, in accordance with the procedures described in Boeing
Service Bulletin 747-53A2312, Revision 2, dated October 8, 1992; or
Revision 3, dated February 8, 2007; except as provided by paragraph
(u) of this AD. As of the effective date of this AD, only Revision 3
shall be used. For purposes of complying with the requirements of
this paragraph, fastener locations that were previously modified in
accordance with paragraph (g) or (n) of this AD do not need to be
modified again. Accomplishment of this modification terminates the
repetitive inspections required by paragraph (m) of this AD for the
modified fastener locations.
Post-Modification Inspections for All Airplanes
(p) For all airplanes: Prior to the accumulation of 10,000 total
landings following the modification required by paragraph (g), (n),
(o), (q) or (s) of this AD, perform an HFEC inspection to detect
cracking at all fastener locations where a countersunk fastener was
found during the inspection required by paragraph (j) or (q)(1) of
this AD, and repeat this inspection thereafter at intervals not to
exceed 4,000 landings, in accordance with the procedures described
in Boeing Service Bulletin 747-53A2312, Revision 2, dated October 8,
1992; or Revision 3, dated February 8, 2007; except as provided by
paragraph (u) of this AD. As of the effective date of this AD, only
Revision 3 shall be used.
New Requirements of This AD
General Visual Inspection for Countersunk Fasteners and Modification
for Model 747SP Airplanes at Stringers S-34L, S-34R, S-40L, S-40R, and
S-46L
(q) For Model 747SP series airplanes having line numbers 201
through 814 inclusive, do the actions in paragraphs (q)(1) and
(q)(2) of this AD at the times specified in those paragraphs.
(1) Prior to the accumulation of 11,000 total landings, or
within 1,000 landings as of the effective date of this AD, whichever
occurs later, unless previously accomplished within the last 3,000
landings prior to the effective date of this AD, conduct a general
visual inspection of the lap joint from BS 1640 to 1901 at S-46L,
and from BS 1741 to 1901 at S-34L, S-34R, S-40L, and S-40R, to
determine if countersunk fasteners have been installed in the
specified area, in accordance with the procedures described in
Boeing Alert Service Bulletin 747-53A2312, Revision 3, dated
February 8, 2007; except as provided by paragraph (u) of this AD.
(i) If no countersunk fastener is found in the upper row of the
lap joint during the inspection, no further action is required by
this AD for the lap joint.
(ii) If any countersunk fastener is found in the upper row of
the lap joint, prior to further flight, perform an HFEC inspection
to detect cracking at all fastener locations where a countersunk
fastener was found, in accordance with the procedures described in
Boeing Alert Service Bulletin 747-53A2312, Revision 3, dated
February 8, 2007; except as provided by paragraph (u) of this AD.
(A) If no cracking is found, repeat the inspection thereafter in
accordance with the requirements of paragraph (m) of this AD.
(B) If any cracking is found, prior to further flight, repair
and modify the lap joint as required by paragraph (n) of this AD.
(2) Prior to the accumulation of 20,000 total landings, or
within 1,000 landings as of the effective date of this AD, whichever
occurs later, modify all fastener locations where a countersunk
fastener was found, during the inspection required by paragraph
(q)(1) of this AD, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2312, Revision
3, dated February 8, 2007; except as provided by paragraph (u) of
this AD. For purposes of complying with the requirements of this AD,
fastener locations that were previously modified in accordance with
paragraph (n) of this AD do not need to be modified again.
Accomplishment of this modification terminates the repetitive
inspections required by paragraph (m) of this AD for the modified
fastener locations.
Adjustments to Compliance Time: Cabin Differential Pressure
(r) For the purposes of calculating the compliance threshold and
repetitive intervals for actions required by paragraphs (f) and (g)
of this AD, as of the effective date of this AD: All flight cycles,
including the number of flight cycles in which cabin differential
pressure is at 2.0 psi or less, must be counted when determining the
number of flight cycles that have occurred on the airplane, and a
1.2 adjustment factor may not be used. However, for airplanes on
which the repetitive intervals for the actions required by paragraph
(f) of this AD have been calculated in accordance with paragraphs
(h) and/or (i) of this AD by excluding the number of flight cycles
in which cabin differential pressure is at 2.0 pounds psi or less,
and/or by using a 1.2 adjustment factor: Continue to adjust the
repetitive intervals in accordance with paragraphs (h) and/or (i) of
this AD until the next inspection required by paragraph (f) of this
AD is accomplished. Thereafter, no adjustment to compliance times
based on paragraphs (h) and/or (i) of this AD is allowed.
Special One-Time Inspection for Cracking of Certain Airplanes
(s) For airplanes with line numbers 630 through 814 inclusive
that meet the conditions specified in paragraphs (s)(1) and (s)(2)
of this AD: Within 300 flight cycles after the effective date of
this AD, or within 500 flight cycles after the most recent sliding
probe inspection done in accordance with Boeing Alert Service
Bulletin 747-53A2312, Revision 1, dated March 29, 1990; or Revision
2, dated October 8, 1992; whichever occurs later, do a special one-
time HFEC inspection or a special one-time detailed inspection for
cracking, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2312, Revision 3, dated
February 8, 2007. If any cracking is found in a lap joint, before
further flight, repair and modify that lap joint in accordance with
Boeing Alert Service Bulletin 747-53A2312, Revision 3, dated
February 8, 2007; except as provided by paragraph (u) of this AD.
Accomplishment of this repair and modification terminates the
repetitive inspections required by paragraph (m) of this AD for that
lap joint. This special one-time inspection is not required for lap
joints that have been modified in accordance with paragraph (g),
(n), (o), or (q) of this AD.
(1) Airplanes that have not been modified in accordance with
paragraph (g) or (o) of this AD.
(2) Airplanes on which the sliding probe HFEC inspection method
specified in Boeing Alert Service Bulletin 747-53A2312, Revision 1,
dated March 29, 1990; or Revision 2, dated October 8, 1992; was used
during the last skin inspection required by paragraph (f), (l), or
(m) of this AD.
Actions After the Special One-time Inspection if No Cracking Is Found
(t) For airplanes specified in paragraph (s) of this AD on which
no cracking is found during the special one-time inspection, do the
applicable repetitive inspections specified in paragraph (t)(1) or
(t)(2) of this AD.
(1) If the special one-time inspection was done using the HFEC
inspection method in accordance with paragraph (s) of this AD,
perform the next inspection required by paragraph (m) of this AD
within the next 4,000 flight cycles after doing the inspection
required by paragraph (s) of this AD, and repeat the inspection
thereafter in accordance with paragraph (m) of this AD.
(2) If the special one-time inspection was done using the
detailed inspection method in accordance with paragraph (s) of this
AD, perform the next inspection required by paragraph (m) of this AD
within the next 500 flight cycles after doing the inspection
required by paragraph (s) of this AD, and repeat the inspection
thereafter in accordance with paragraph (m) of this AD.
Contacting the Manufacturer
(u) Where Boeing Alert Service Bulletin 747-53A2312, Revision 3,
dated February 8, 2007, specifies to contact Boeing for appropriate
action for a repair or inspection, before further flight, do the
applicable action in paragraph (u)(1) or (u)(2) of this AD.
(1) Do the repair using a method approved in accordance with the
procedures specified in paragraph (v) of this AD.
(2) Do the inspection using a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA. For a repair
method to be approved by the Manager, Seattle ACO, as required by
this paragraph, the Manager's approval letter must specifically
refer to this AD.
[[Page 47039]]
Alternative Methods of Compliance (AMOCs)
(v)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(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 appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) An AMOC that provides an acceptable level of safety shall be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who 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 94-15-06 for
airplane line numbers 630 through 814 inclusive are approved as
AMOCs for the corresponding provisions of this AD if the AMOC does
not involve using the existing sliding probe HFEC skin inspection
method specified in Boeing Service Bulletin 747-53A2312, Revision 2,
dated October 8, 1992, or an earlier version. In addition, the
provisions of paragraph (r) of this AD must be applied to AMOCs
approved previously in accordance with AD 94-15-06, where
applicable.
(5) AMOCs approved previously in accordance with AD 94-15-06 for
airplane line numbers 201 through 629 inclusive are approved as
AMOCs for the corresponding provisions of this AD. In addition, the
provisions of paragraph (r) of this AD must be applied to AMOCs
approved previously in accordance with AD 94-15-06, where
applicable.
Material Incorporated by Reference
(w) You must use Boeing Alert Service Bulletin 747-53A2312,
dated June 12, 1989; Boeing Service Bulletin 747-53A2312, Revision
1, including ``Addendum,'' dated March 29, 1990; Boeing Service
Bulletin 747-53A2312, including the ``Addendum,'' Revision 2, dated
October 8, 1992; or Boeing Service Bulletin 747-53A2312, Revision 3,
dated February 8, 2007; as applicable; to perform the actions that
are required by this AD, unless the AD specifies otherwise. (The
document number and date of Boeing Alert Service Bulletin 747-
53A2312, dated June 12, 1989, are identified only on the first page
of the document; no other page of the document contains this
information.)
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2312, dated June 12, 1989; Boeing Service Bulletin 747-53A2312,
Revision 1, including ``Addendum,'' dated March 29, 1990; and Boeing
Service Bulletin 747-53A2312, Revision 3, dated February 8, 2007; in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On August 24, 1994 (59 FR 37659, July 25, 1994), the
Director of the Federal Register approved the incorporation by
reference of Boeing Service Bulletin 747-53A2312, including the
``Addendum,'' Revision 2, dated October 8, 1992.
(3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or 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:
http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on July 23, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-17776 Filed 8-12-08; 8:45 am]
BILLING CODE 4910-13-P