[Federal Register: October 4, 2005 (Volume 70, Number 191)]
[Rules and Regulations]
[Page 57740-57746]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr04oc05-9]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20917; Directorate Identifier 2004-NM-85-AD;
Amendment 39-14312; AD 2005-20-18]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, -200B, -200F, -
200C, -100B, -300, -100B SUD, -400, -400D, and -400F Series Airplanes;
and Model 747SR Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding two existing airworthiness directives
(AD), which apply to certain Boeing transport category airplanes. One
AD currently requires doing certain inspections to detect cracks and
corrosion around the lower bearing of the actuator attach fittings of
the inboard and outboard flaps; repairing if necessary; and either
overhauling the fittings or replacing them, which ends certain
repetitive inspections. The other AD currently requires certain other
inspections to detect discrepancies of the actuator attach fittings of
the flaps, and follow-on and corrective actions if necessary, which
ends the repetitive inspections of the first AD. For certain airplanes,
this AD requires new inspections for discrepancies of the actuator
attach fittings of the flaps, and follow-on and corrective actions if
necessary, which ends the repetitive inspections of both existing ADs.
For all airplanes, this AD requires repetitive overhaul/replacements of
the actuator attach fittings of both the inboard and outboard flaps.
This AD results from reports of cracks of the actuator attach fittings
of the trailing edge flaps. We are issuing this AD to prevent cracking
and other damage of the actuator attach fittings of the trailing edge
flaps, which could result in abnormal operation or
[[Page 57741]]
retraction of a trailing edge flap, and possible loss of
controllability of the airplane.
DATES: This AD becomes effective November 8, 2005.
On May 8, 2003 (68 FR 19937, April 23, 2003), the Director of the
Federal Register approved the incorporation by reference of Boeing
Alert Service Bulletin 747-57A2316, dated December 19, 2002.
On August 3, 2001 (66 FR 34526, June 29, 2001), the Director of the
Federal Register approved the incorporation by reference of Boeing
Service Bulletin 747-57A2310, Revision 1, dated November 23, 1999; and
Boeing Service Bulletin 747-57A2310, Revision 2, dated February 22,
2001.
ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov
or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., Nassif Building,
room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6443; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at http://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2001-13-12, amendment
39-12292 (66 FR 34526, June 29, 2001), and AD 2003-08-11, amendment 39-
13124 (68 FR 19937, April 23, 2003). AD 2001-13-12 applies to certain
Boeing Model 747 series airplanes. AD 2003-08-11 applies to all Boeing
Model 747-100, -200B, -200F, -200C, -100B, -300, -100B SUD, -400, -
400D, and -400F series airplanes; and Model 747SR series airplanes.
That NPRM was published in the Federal Register on April 13, 2005 (70
FR 19345). That NPRM proposed to continue to require the existing
requirements of ADs 2001-13-12, and 2003-08-11. For certain airplanes,
that NPRM also proposed to require new inspections for discrepancies of
the actuator attach fittings of the flaps, and follow-on and corrective
actions if necessary, which ends the repetitive inspections of both
existing ADs. For all airplanes, that NPRM also proposed to require
repetitive overhaul/replacements of the fittings of both the inboard
and outboard flaps.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request for Clarification
One commenter, the airplane manufacturer, requests that paragraph
(r) of the NPRM be revised to apply to ``fittings'' instead of
``airplanes.'' The commenter states that some operators may have
complied with paragraph (o)(2) of the NPRM for some fittings, but not
others. The commenter also states that the proposed actions in
paragraph (r) are not necessary if the proposed actions in paragraph
(o)(2) have been done. The commenter also requests that paragraph (r)
be revised to clarify this point.
We partially agree. We agree with the commenter to refer to
``fittings'' rather than ``airplanes'' in paragraph (r) and have
revised the final rule accordingly. However, we do not agree that
paragraph (r) needs to be clarified regarding paragraph (o)(2).
Although the actions specified in paragraph (o)(2) (refers to Parts 2
through 5 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2316, dated December 19, 2002) are identical to those
in paragraphs (r) and (s), the affected fittings and compliance times
in those paragraphs are different.
Paragraph (r) states, ``For [fittings] on which * * * the
inspections required by [paragraph] (m), (n), or (o)(1) of this AD are
being done as of the effective date of this AD.'' The actions specified
in paragraphs (m), (n), and (o)(1) are done in accordance with Part 1
of the Accomplishment Instructions of the referenced service bulletin.
Paragraph (r) does not apply to fittings on which the actions specified
in paragraph (o)(2) (i.e., Parts 2 through 5) are being done. Operators
doing the actions specified in paragraph (o)(2) instead of the actions
specified in paragraph (o)(1), must continue to do those actions at the
specified times in paragraph (o)(2). Operators doing the actions in
paragraph (o)(1) of this AD as of the effective date of this AD, must
do the requirements of paragraph (r). We have made no change to the
final rule in this regard.
The same commenter notes that paragraph (t) of the NPRM states,
``at the applicable time specified in Figures 1 and 2 of the service
bulletin.'' The commenter requests that the reference to Figure 2 in
that paragraph be deleted, because Figure 2 does not specify compliance
times.
We agree and have revised paragraph (t) accordingly.
Explanation of Editorial Changes
Based on the comment above that fittings may be overhauled at
different times, we have clarified the terminating action in paragraphs
(j)(1) and (j)(2) of the NPRM. Overhauling an actuator attach fitting
on an applicable flap constitutes terminating action for the repetitive
inspection requirements for that fitting. The remaining fittings that
are not being repetitively overhauled must be repetitively inspected.
Therefore, we have revised paragraphs (j)(1) and (j)(2) of this AD
accordingly.
Paragraph (r) of the NPRM applies to fittings on which the
repetitive borescopic, detailed, ``or'' ultrasonic (as applicable)
inspections required by paragraph (m), (n), or (o)(1) of this AD are
being done as of the effective date of this AD. Paragraph (m) of the
NPRM proposed to require both borescopic and detailed inspections.
Paragraph (n) of the NPRM proposed to require borescopic, detailed, and
ultrasonic inspections. Paragraph (o)(1) of the NPRM proposed to
require applicable inspections specified in paragraphs (m) and (n). It
was our intent that paragraph (r) apply to fittings on which the
repetitive borescopic, detailed, ``and'' ultrasonic (as applicable)
inspections required by paragraph (m), (n), or (o)(1) of this AD are
being done as of the effective date of this AD. Therefore, we have
revised paragraph (r) accordingly.
Boeing Commercial Airplanes has received a Delegation Option
Authorization (DOA). We have revised this AD to delegate the authority
to approve an alternative method of compliance for any repair required
by this AD to an Authorized Representative for the Boeing Commercial
Airplanes DOA rather than a Designated Engineering Representative.
Although paragraph (s) of the NPRM states, ``except as provided by
paragraph (u) of this AD,'' paragraph (u) does not refer to paragraph
(s). We have corrected this mistake in this AD.
[[Page 57742]]
Although paragraph (t) of the NPRM states, ``except as provided by
paragraph (v) of this AD,'' paragraph (v) incorrectly refers to
paragraph (s) rather than paragraph (t). In addition, paragraph (t)
states, ``If any discrepancy is detected during any inspection required
by paragraph (r) * * *'' The requirements of paragraph (t) also are
required if any discrepancy is detected during an inspection required
by paragraph (s), as specified in Boeing Alert Service Bulletin 747-
57A2316, described in the preamble of the NPRM. We have corrected these
mistakes in this AD.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have added a new paragraph (y)(2) and renumbered subsequent
paragraphs to clarify the appropriate procedure for notifying the
principal inspector before using any approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
This AD will affect about 1,000 Model 747-100, -200B, -200F, -200C,
-100B, -300, -100B SUD, -400, -400D, and -400F series airplanes; and
Model 747SR series airplanes worldwide. There are about 181 airplanes
on the U.S. registry. The average labor rate is $65 per hour. The
following two tables provide the estimated costs for U.S. operators to
comply with this AD.
Table 1.--Estimated Costs
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Work
Action hours Parts Cost per airplane Fleet cost
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Inspections (required by AD 2001-13- 2 None................ $130, per inspection $23,530, per
12). cycle. inspection cycle.
Inspections specified in Part 1 of 2 None................ $130 per inspection $23,530 per
the Accomplishment Instruction cycle. inspection cycle.
(AI) of the referenced service
bulletin (required by AD 2003-08-
11).
Inspections specified in Part 2 of 5 None................ $325 per inspection $58,825 per
the AI of the referenced service cycle. inspection cycle.
bulletin (new proposed actions).
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Table 2.--Estimated Costs
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Work
Action hours Parts Cost per airplane
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Overhaul(s) as an alternative to the 37 None........................... $2,405.
replacement.
Replacement(s) as an alternative to the 4 $6,623 (for the four actuator $6,883 (for the four actuator
overhaul. attach fittings on the attach fittings on the
outboard flaps) and $7,566 outboard flaps) and $7,826
(for the four actuator attach (for the four actuator attach
fittings on the inboard flaps). fittings on the inboard
flaps), per replacement
cycle.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this 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.s
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 amendments 39-12292 (66 FR 34526, June 29, 2001) and 39-13124
(68 FR 19937, April 23, 2003) and by adding the following new
airworthiness directive (AD):
[[Page 57743]]
2005-20-18 Boeing: Amendment 39-14312. Docket No. FAA-2005-20917;
Directorate Identifier 2004-NM-85-AD.
Effective Date
(a) This AD becomes effective November 8, 2005.
Affected ADs
(b) This AD supersedes AD 2001-13-12, amendment 39-12292; and AD
2003-08-11, amendment 39-13124.
Applicability
(c) This AD applies to all Boeing Model 747-100, -200B, -200F, -
200C, -100B, -300, -100B SUD, -400, -400D, and -400F series
airplanes; and Model 747SR series airplanes; certificated in any
category.
Unsafe Condition
(d) This AD results from reports of cracks of the actuator
attach fittings of the trailing edge flaps. We are issuing this AD
to prevent cracking and other damage of the actuator attach fittings
of the trailing edge flaps, which could result in abnormal operation
or retraction of a trailing edge flap, and possible loss of
controllability of the airplane.
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 2001-13-12
Affected Airplanes
(f) For Boeing Model 747 series airplanes, as listed in Boeing
Service Bulletin 747-57A2310, Revision 2, dated February 22, 2001,
do the actions required by paragraphs (g) through (l) of this AD, as
applicable.
Actuator Attach Fittings That Have Not Been Overhauled or Replaced
(g) For actuator attach fittings on the outboard flaps that have
not been overhauled in accordance with revisions of Boeing 747
Overhaul Manual (OHM) 57-52-55 dated prior to June 1, 1999, or
replaced with a new fitting, prior to August 3, 2001 (the effective
date of AD 2001-13-12); and for actuator attach fittings on the
inboard flap actuators that have not been overhauled in accordance
with revisions of OHM 57-52-35, dated prior to June 1, 1999, or
replaced with a new fitting, prior to August 3, 2001: Accomplish the
actions in paragraph (i), (j), or (k) of this AD at the later of the
times specified in paragraphs (g)(1) and (g)(2) of this AD.
(1) Prior to the accumulation of 8 years since date of
manufacture or 8,000 total flight cycles, whichever occurs first.
(2) Within 6 months after August 3, 2001.
Actuator Attach Fittings That Have Been Overhauled or Replaced
(h) For actuator attach fittings on the outboard flaps that have
been overhauled in accordance with revisions of OHM 57-52-55 dated
prior to June 1, 1999, or replaced with a new fitting, prior to
August 3, 2001; and for actuator attach fittings on the inboard flap
actuators that have been overhauled in accordance with revisions of
OHM 57-52-35 dated prior to June 1, 1999, or replaced with a new
fitting, prior to August 3, 2001: Accomplish the actions in
paragraph (i), (j), or (k) of this AD at the later of the times
specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Within 8 years or 8,000 total flight cycles after the attach
fitting was overhauled or replaced, whichever occurs first.
(2) Within 6 months after August 3, 2001.
Inspections and Corrective Action
(i) Perform a detailed inspection to detect corrosion around the
lower bearing journal on the actuator attach fittings on the inboard
and outboard flaps, and perform an ultrasonic inspection to detect
cracks around the lower bearing journal of the actuator attach
fittings on the outboard flaps, in accordance with Boeing Service
Bulletin 747-57A2310, Revision 1, dated November 23, 1999; or
Revision 2, dated February 22, 2001.
Note 1:
For the purposes of this AD, a detailed inspection is: ``An
intensive examination of a specific item, installation, or assembly
to detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at an
intensity deemed appropriate. Inspection aids such as mirror,
magnifying lenses, etc., may be necessary. Surface cleaning and
elaborate procedures may be required.''
Note 2:
Inspections, overhauls, and replacements accomplished in
accordance with Boeing Alert Service Bulletin 747-57A2310, dated
June 17, 1999, are acceptable for compliance with the requirements
of paragraph (i) of this AD.
(1) If no corrosion or cracks are detected, repeat the
inspections required by paragraph (i) of this AD at intervals not to
exceed 18 months. Within 5 years after the initial inspections
required by paragraph (i) of this AD, accomplish the actions
specified in paragraph (j) or (k) of this AD.
(2) If any corrosion is detected, prior to further flight,
remove the corrosion by accomplishing the actions of either
paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
(i) If corrosion is within the limits of the Boeing 747 OHM:
Prior to further flight, accomplish the actions specified in
paragraph (j) or (k) of this AD.
(ii) If corrosion is not within the limits of the Boeing 747
OHM: Prior to further flight, accomplish the actions specified in
paragraph (k) or (l) of this AD.
(3) If any crack is detected: Prior to further flight,
accomplish the actions specified in paragraph (k) or (l) of this AD.
Overhaul
(j) Do the actions as specified in paragraphs (j)(1) and (j)(2)
of this AD in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-57A2310, Revision 1, dated November 23,
1999; or Revision 2, dated February 22, 2001.
(1) Overhaul the actuator attach fittings on the outboard flaps.
Repeat the overhaul of the fittings on the outboard flaps as
specified in Part 2 of the Work Instructions of the service bulletin
thereafter at intervals not to exceed 8 years or 8,000 flight
cycles, whichever occurs first. As of the effective date of this AD,
the repetitive overhauls must be done in accordance with Part 5 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2316, dated December 19, 2002, at intervals not to exceed 8
years since last overhaul. Overhauling an actuator attach fitting on
an outboard flap constitutes terminating action for the repetitive
inspection requirements of paragraph (i)(1) of this AD for that
fitting.
(2) Overhaul the actuator attach fittings on the inboard flaps.
Overhauling an actuator attach fitting on an inboard flap
constitutes terminating action for the requirements of paragraphs
(g) through (l) of this AD for that fitting.
Replacement
(k) Replace the actuator attach fittings on the inboard and
outboard flaps in accordance with paragraph (k)(1) or (k)(2) of this
AD.
(1) Replace the actuator attach fittings on the inboard and
outboard flaps with new actuator attach fittings in accordance with
``Part 3--Replacement'' of Boeing Service Bulletin 747-57A2310,
Revision 1, dated November 23, 1999; or Revision 2, dated February
22, 2001. Accomplishment of this replacement constitutes terminating
action for the repetitive inspections required by paragraph (i) of
this AD for the replaced fitting. Within 8 years or 8,000 flight
cycles following accomplishment of the replacement, whichever occurs
first, repeat this replacement or accomplish the overhaul specified
in paragraph (j) of this AD. As of the effective date of this AD,
the repetitive replacements must be done in accordance with Part 5
of the Accomplishment Instructions of Boeing Alert Service Bulletin
747-57A2316, dated December 19, 2002, at intervals not to exceed 8
years since last replacement.
(2) Replace the actuator attach fittings on the inboard and
outboard flaps with improved actuator attach fittings in accordance
with ``Part 4--Terminating Action'' of Boeing Service Bulletin 747-
57A2310, Revision 2, dated February 22, 2001. If accomplished, this
replacement with improved fittings terminates the requirements of
paragraphs (g) through (l) of this AD for the replaced fitting.
Note 3: Replacement of the actuator attach fittings on the
inboard flaps with fittings that have been overhauled before the
effective date of this AD, in accordance with Boeing OHM 57-52-35,
Temporary Revision 57-8, dated June 10, 1999; Temporary Revision 57-
10, dated May 8, 2000; or Full Revision 57-10, dated July 1, 2000;
constitutes terminating action for the requirements of paragraphs
(g) through (l) of this AD for the actuator attach fittings on the
inboard flaps.
Repair
(l) During any inspection done in accordance with paragraph (i)
of this AD, if corrosion is found that is outside the limits
specified in the Boeing 747 OHM, or if any crack is detected: In
lieu of replacement of the actuator attach fittings in accordance
with paragraph (k) of this AD, repair the actuator attach fittings
on the inboard and outboard flaps in accordance with a method
[[Page 57744]]
approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA; or using a method approved in accordance with paragraph
(y)(3) of this AD.
Requirements of AD 2003-08-11
Inspection: Inboard Flap Actuator Attach Fittings
(m) Perform borescopic and detailed inspections to detect
discrepancies of the actuator attach fittings of the inboard flap ,
in accordance with Part 1 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002.
Discrepancies include corrosion, pitting, and damaged or missing
cadmium plating. Do the inspection at the applicable time specified
in paragraph (m)(1) or (m)(2) of this AD.
(1) If the age of the fittings can be determined: Inspect within
14 years since the fittings were new or last overhauled, or within
90 days after May 8, 2003 (the effective date of AD 2003-08-11),
whichever occurs later.
(2) If the age of the fittings cannot be determined: Inspect
within 90 days after May 8, 2003.
Note 4: The exceptions specified in flag note 4 of Figure 1 of
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002,
apply to the requirements of paragraphs (m) and (n) of this AD.
Inspection: Outboard Flap Actuator Attach Fittings
(n) Perform borescopic, detailed, and ultrasonic inspections to
detect discrepancies of the actuator attach fittings of the outboard
flap , in accordance with Part 1 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2316, dated December 19,
2002. Discrepancies include surface corrosion, pitting, damaged or
missing cadmium plating, and cracks. Do the inspection at the
applicable time specified in paragraph (n)(1) or (n)(2) of this AD.
(1) If the age of the fittings can be determined: Inspect within
8 years since the fittings were new or last overhauled, or within 90
days after May 8, 2003, whichever occurs later.
(2) If the age of the fittings cannot be determined: Inspect
within 90 days after May 8, 2003.
Follow-on Actions: No Discrepancies Found
(o) If no discrepancy is found during any inspection required by
paragraph (m) through (p) of this AD: Do the actions specified by
either paragraph (o)(1) or paragraph (o)(2) of this AD.
(1) Repeat the applicable inspections specified in paragraphs
(m) and (n) of this AD at intervals not to exceed 9 months until the
actions specified in paragraph (o)(2) of this AD have been
accomplished.
(2) Perform a detailed inspection of the fitting to detect
cracks, corrosion, damaged cadmium plating, or bushing migration, in
accordance with and at the time specified in Part 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2316, dated December 19, 2002. Do the follow-on actions in
accordance with Parts 3, 4, and 5 of the Accomplishment Instructions
of the service bulletin at the times specified in Figure 1 of the
service bulletin, as applicable. Accomplishment of these actions
terminates the initial and repetitive inspection requirements of
paragraphs (m), (n), and (o)(1) of this AD.
Note 5: The exceptions specified in flag note 2 of Figure 1 of
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002,
apply to those requirements of paragraphs (o)(2) and (p) of this AD
that are specified in Part 2 of the service bulletin.
Corrective/Follow-on Actions: Discrepancies Found
(p) If any discrepancy is found during any inspection required
by paragraph (m), (n), or (o) of this AD: Perform applicable
corrective and follow-on actions at the time specified and in
accordance with Figure 1 of Boeing Alert Service Bulletin 747-
57A2316, dated December 19, 2002. Before further flight: Replace any
discrepant fitting in accordance with Part 5 of the Accomplishment
Instructions of the service bulletin, and accomplish the follow-on
actions for the other fittings common to that flap in accordance
with Part 2 of the Accomplishment Instructions of the service
bulletin. Replacement of a fitting terminates the initial and
repetitive inspections--specified in paragraphs (m), (n), and (o) of
this AD--for that fitting only.
Terminating Action for Certain Requirements
(q) Accomplishment of the actions required by paragraphs (m) and
(n) of this AD ends the requirements of paragraphs (g) through (k)
of this AD, except for the repetitive overhauls and repetitive
replacements required by paragraphs (j)(1) and (k)(1) of this AD,
respectively.
New Actions Required by This AD
Inspections: Actuator Attach Fittings of the Inboard and Outboard
Flaps
(r) For fittings on which the repetitive borescopic, detailed,
and ultrasonic (as applicable) inspections required by paragraph
(m), (n), or (o)(1) of this AD are being done as of the effective
date of this AD: Inspect as specified in Table 1 of this AD.
Accomplishing these actions ends the initial and repetitive
inspections required by paragraphs (m), (n), and (o)(1) of this AD.
Table 1.--Inspections of Actuator Attach Fittings
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Requirements Description
------------------------------------------------------------------------
(1) Compliance time: Except as provided by paragraph (u) of
this AD, at the applicable time
specified in Figure 1 of Boeing Alert
Service Bulletin 747-57A2316, dated
December 19, 2002.
(2) Area to inspect: The actuator attach fittings of the
inboard and outboard flaps.
(3) Type of inspection: Detailed inspection (inboard and outboard
flaps) and ultrasonic inspection
(outboard flaps only).
(4) Discrepancies to detect: Surface corrosion, pitting, cracks,
migrated or rotated bushings, and
damaged or missing cadmium plating.
(5) In accordance with: Part 2 of the Work Instructions of Boeing
Alert Service Bulletin 747-57A2316,
dated December 19, 2002.
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Follow-on Actions: No Discrepancies Detected
(s) If no discrepancy is detected during any inspection required
by paragraph (r) of this AD: Do the follow-on actions in accordance
with Parts 3, 4, and 5, as applicable, of the Work Instructions of
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002,
at the applicable times specified in Figure 1 of the service
bulletin, except as provided by paragraph (u) of this AD.
Overhaul/Replacement and Follow-on/Corrective Actions:
Discrepancies Detected
(t) If any discrepancy is detected during any inspection
required by paragraph (r) or (s) of this AD: Do the actions
specified in Table 2 of this AD at the applicable times specified in
Figure 1 of the service bulletin, except as provided by paragraph
(v) of this AD.
[[Page 57745]]
Table 2.--Discrepancies Found
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In accordance with Boeing Alert
Requirements Service Bulletin 747-57A2316,
dated December 19, 2002--
------------------------------------------------------------------------
(1) Overhaul or replace discrepant Part 5 of Work Instructions.
fitting with new fitting.
(2) Do the follow-on and corrective Parts 2 and 5 of Work
actions for the other fitting common Instructions, as applicable.
to that flap, except as specified in
flag note 2 in Figure 1 of the service
bulletin.
------------------------------------------------------------------------
Compliance Time Requirements
(u) For the requirements of paragraphs (r) and (s) of this AD:
Where Figure 1 of Boeing Alert Service Bulletin 747-57A2316, dated
December 19, 2002, states a compliance time ``after the original
issue date of the service bulletin,'' this AD requires compliance
within the applicable compliance time after the effective date of
this AD.
(v) For the requirements of paragraph (t) of this AD: Where
Figure 1 of Boeing Alert Service Bulletin 747-57A2316, dated
December 19, 2002, specifies to repeat the overhaul or replacement
``every 8 years,'' this AD requires compliance at intervals not to
exceed 8 years.
Repetitive Overhaul or Replacement
(w) Except as provided in paragraph (x) of this AD, at the
applicable time specified in paragraph (w)(1) or (w)(2) of this AD,
overhaul the actuator attach fittings on the outboard and inboard
flaps or replace the actuator attach fittings with new or overhauled
fittings, in accordance with Part 5 of the Work Instructions of
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002.
Repeat the overhaul or replacement thereafter at intervals not to
exceed 8 years.
(1) If the age of the fittings can be determined: Overhaul or
replace within 8 years since the fittings were new or last
overhauled, or within 2 years after the effective date of this AD,
whichever occurs later.
(2) If the age of the fittings cannot be determined: Assume that
the fittings are more than 14 years old, and overhaul or replace
within 2 years after the effective date of this AD.
(x) Accomplishing the repetitive overhauls required by paragraph
(j)(1) or repetitive replacements required by paragraph (k)(1) of
this AD is acceptable for compliance with the requirements of
paragraph (w) of this AD.
Alternative Methods of Compliance (AMOCs)
(y)(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) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
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 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 2001-13-12
are approved as AMOCs with the actions required by paragraphs (g)
through (l) of this AD, as applicable. However, AMOCs approved
previously are not considered terminating action for the repetitive
overhauls or replacements requirements of this AD.
(5) AMOCs approved previously in accordance with AD 2003-08-11
are approved as AMOCs with the actions required by paragraphs (m)
through (p) of this AD, as applicable.
Material Incorporated by Reference
(z) You must use the service bulletin in Table 3 of this AD to
perform the actions that are required by this AD, unless the AD
specifies otherwise.
(1) On May 8, 2003 (68 FR 19937, April 23, 2003), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002.
(2) On August 3, 2001 (66 FR 34526, June 29, 2001), the Director
of the Federal Register approved the incorporation by reference of
Boeing Service Bulletin 747-57A2310, Revision 1, dated November 23,
1999; and Boeing Service Bulletin 747-57A2310, Revision 2, dated
February 22, 2001.
(3) Contact Boeing Commercial Airplanes, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention:
Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of
this service information. You may review copies at the Docket
Management Facility, U.S. Department of Transportation, 400 Seventh
Street SW., room PL-401, Nassif Building, Washington, DC; on the
Internet at http://dms.dot.gov; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Table 3.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Revision
Service bulletin level Date
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 747-57A2316...... Original December 19, 2002.
Boeing Service Bulletin 747-57A2310............ 1 November 23, 1999.
Boeing Service Bulletin 747-57A2310............ 2 February 22, 2001.
----------------------------------------------------------------------------------------------------------------
[[Page 57746]]
Issued in Renton, Washington, on September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-19876 Filed 10-3-05; 8:45 am]
BILLING CODE 4910-13-P