Airworthiness Directives; Boeing Model 747 Airplanes, 39644-39647 [05-13432]
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39644
Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. To get copies of
the service information, contact Empresa
Brasileira de Aeronautica S.A. (EMBRAER),
P.O. Box 343—CEP 12.225, Sao Jose dos
Campos—SP, Brazil. To view the AD docket,
go to the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., room PL–401, Nassif Building,
Washington, DC. To review copies of the
service information, go to 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 https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on June 29,
2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–13431 Filed 7–8–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20243; Directorate
Identifier 2004–NM–153–AD; Amendment
39–14185; AD 2005–14–08]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
747–100, –200, –300, and 747SP series
airplanes. That AD currently requires
certain inspections to find missing or
alloy-steel taperlock fasteners (bolts) in
the diagonal brace underwing fittings,
and corrective actions if necessary. For
airplanes with missing or alloy-steel
fasteners, that AD also mandates
replacement of certain fasteners with
new fasteners, which constitutes
terminating action for certain
inspections. This new AD expands the
applicability to include additional
airplane models and requires a new
inspection to determine fastener
material and to find missing or broken
fasteners, and related investigative/
corrective actions if necessary. This AD
is prompted by reports indicating that
cracked fasteners made of A286 material
were found on airplanes that had only
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12:58 Jul 08, 2005
Jkt 205001
fasteners made of A286 material
installed in the area common to the
diagonal brace underwing fittings. We
are issuing this AD to prevent loss of the
underwing fitting load path due to
missing or damaged alloy-steel or A286
taperlock fasteners, which could result
in separation of the engine and strut
from the airplane.
DATES: This AD becomes effective
August 15, 2005.
The incorporation by reference of
Boeing Alert Service Bulletin 747–
57A2312, Revision 1, dated April 29,
2004, is approved by the Director of the
Federal Register as of August 15, 2005.
On August 1, 2001 (66 FR 34094, June
27, 2001), the Director of the Federal
Register approved the incorporation by
reference of Boeing Alert Service
Bulletin 747–57A2312, dated June 15,
2000.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the AD
docket on the Internet at https://
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 U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
Washington, DC. This docket number is
FAA–2005–20243; the directorate
identifier for this docket is 2004–NM–
153–AD.
FOR FURTHER INFORMATION CONTACT:
Nicholas Kusz, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6432; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR
part 39) with an AD to supersede AD
2001–13–06, amendment 39–12286 (66
FR 34094, June 27, 2001). The existing
AD applies to certain Boeing Model
747–100, –200, –300, and 747SP series
airplanes. The proposed AD was
published in the Federal Register on
February 1, 2005 (70 FR 5066), to
continue to require the actions required
by the existing AD. The proposed AD
would also expand the applicability to
include additional airplane models and
would require a new inspection to
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determine fastener material and to find
missing or broken fasteners, and related
investigative/corrective actions if
necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
Support for the Proposed AD
One commenter supports the
proposed AD.
Request To Increase Initial Inspection
Threshold
One commenter requests that we
revise paragraph (h)(1) of the proposed
AD to increase the initial inspection
threshold from 12 months to 18 months
after the effective date of the AD for the
inspection in that paragraph. The
commenter states that this would allow
the inspection to be performed during a
regularly scheduled C-check.
We agree. Our intent was that the
affected fasteners be inspected during a
regularly scheduled maintenance visit
in which time permits the fuel tank to
be opened. We have revised paragraph
(h)(1) of this AD to specify a compliance
threshold of 18 months after the
effective date of the AD.
Request To Clarify Subject Fasteners
One commenter requests that we
revise paragraph (h) to clarify that the
inspections required by that paragraph
apply to the aft-most 10 fasteners in the
diagonal brace underwing fitting, not
‘‘all fasteners in the diagonal brace
underwing fitting,’’ as stated in the
proposed AD. We agree and have
revised paragraph (h) of this AD
accordingly.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, 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
There are about 739 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this AD, at an average
labor rate of $65 per work hour.
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Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations
39645
ESTIMATED COSTS
Action
Work hours
Detailed and magnetic inspection (required by AD 2001–13–06) ...
Detailed and magnetic inspections (new requirement) ....................
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. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
12:58 Jul 08, 2005
Jkt 205001
None .................
None .................
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–12286 (66 FR
34094, June 27, 2001) and by adding the
following new airworthiness directive
(AD):
I
2005–14–08 Boeing: Amendment 39–14185.
Docket No. FAA–2005–20243;
Directorate Identifier 2004–NM–153–AD.
Effective Date
(a) This AD becomes effective August 15,
2005.
Affected ADs
(b) This AD supersedes AD 2001–13–06,
amendment 39–12286.
Applicability
(c) This AD applies to Model 747–100,
747–100B, 747–100B SUD, 747–200B, 747–
200C, 747–200F, 747–300, 747–400, 747–
400D, 747–400F, 747SR, and 747SP series
airplanes; certificated in any category; as
identified in Boeing Alert Service Bulletin
747–57A2312, Revision 1, dated April 29,
2004.
Unsafe Condition
(d) This AD was prompted by reports
indicating that cracked fasteners made of
A286 material were found on airplanes that
had only fasteners made of A286 material
installed in the area common to the diagonal
brace underwing fittings. We are issuing this
AD to prevent loss of the underwing fitting
load path due to missing or damaged alloysteel or A286 taperlock fasteners, which
could result in separation of the engine and
strut from the airplane.
Compliance
List of Subjects in 14 CFR Part 39
VerDate jul<14>2003
2
3
Adoption of the Amendment
Authority for This Rulemaking
(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.
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Cost per
airplane
Parts
Number of
U.S.-registered
airplanes
$130
195
60
140
Fleet cost
$7,800
27,300
Requirements of AD 2001–13–06
Repetitive Inspections
(f) For Boeing Model 747–100, 747–200,
747–300, and 747SP series airplanes
equipped with titanium diagonal brace
underwing fittings, as identified in Boeing
Alert Service Bulletin 747–57A2312, dated
June 15, 2000: Within 12 months after August
1, 2001 (the effective date of AD 2001–13–06,
amendment 39–12286), do a one-time
detailed inspection of the diagonal brace
underwing fitting at the Number 1 and
Number 4 engine pylons to find missing
taperlock fasteners (bolts), and a magnetic
inspection to find alloy-steel fasteners per
Part 1 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2312,
dated June 15, 2000; or Revision 1, dated
April 29, 2004.
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.’’
(1) If no alloy-steel fasteners are found and
no fasteners are missing, no further action is
required by this paragraph.
(2) If any alloy-steel fasteners are found or
any fasteners are missing, before further
flight, do an ultrasonic inspection of the
alloy-steel fasteners to find damage per Part
2 of the Accomplishment Instructions of the
service bulletin.
(i) If no damaged alloy-steel fasteners are
found, and no fasteners are missing: Repeat
the ultrasonic inspection thereafter at
intervals not to exceed 18 months until
accomplishment of the terminating action
required by paragraph (g) of this AD.
(ii) If any damaged alloy-steel fasteners are
found, or any fasteners are missing: Before
further flight, do an ultrasonic inspection of
all 10 aft fasteners (including non-alloy steel)
per Part 2 of the Accomplishment
Instructions of the service bulletin. Before
further flight, replace damaged and missing
fasteners with new fasteners per Part 3 of the
Accomplishment Instructions of the service
bulletin, except as provided by paragraph (l)
of this AD. Thereafter, repeat the inspection
of the remaining alloy-steel fasteners at
intervals not to exceed 18 months until
accomplishment of the terminating action
required by paragraph (g) or the optional
terminating action specified in paragraph (m)
of this AD.
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39646
Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations
Terminating Action
(g) For Boeing Model 747–100, 747–200,
747–300, and 747SP series airplanes
equipped with titanium diagonal brace
underwing fittings, as identified in Boeing
Alert Service Bulletin 747–57A2312, dated
June 15, 2000: Within 48 months after August
1, 2001, do the actions required by
paragraphs (g)(1) and (g)(2), or (g)(3) of this
AD, per Boeing Alert Service Bulletin 747–
57A2312, dated June 15, 2000; or Revision 1,
dated April 29, 2004. Accomplishment of the
actions specified in this paragraph
constitutes terminating action for the
repetitive inspection requirements of
paragraph (f) of this AD.
(1) Perform an open-hole high frequency
eddy current (HFEC) inspection to detect
cracks, corrosion, or damage at the bolt hole
locations of the aft 10 taperlock fasteners in
the diagonal brace underwing fitting at the
Number 1 and Number 4 engine pylons per
Part 3 of the Accomplishment Instructions of
the service bulletin. If any cracking is
detected, before further flight, perform
applicable corrective actions per the service
bulletin, except as provided by paragraph (l)
of this AD.
(2) Before further flight: Replace all 10 aft
taperlock fasteners with new, improved
fasteners per Part 3 of the Accomplishment
Instructions of the service bulletin.
(3) Do an ultrasonic inspection to find
damaged fasteners per Part 2 of the
Accomplishment Instructions of the service
bulletin. Before further flight, replace all
damaged non-alloy steel and all alloy-steel
fasteners with new fasteners per Part 3 of the
Accomplishment Instructions of the service
bulletin. Do an open-hole HFEC inspection
before installation of the new fasteners; if any
cracking, corrosion, or damage is found,
before further flight, perform applicable
corrective actions per the service bulletin,
except as provided by paragraph (l) of this
AD.
New Requirements of This AD
Inspection for Missing/Broken Fasteners and
to Determine Material Type
(h) For the aft 10 taperlock fasteners in the
diagonal brace underwing fitting at the
Number 1 and Number 4 engine pylons:
Perform the inspections in paragraphs (h)(1)
and (h)(2) of this AD, as applicable.
(1) For airplanes not identified in
paragraph (f) of this AD: Within 18 months
after the effective date of this AD, perform a
detailed inspection to ensure that all
fasteners are installed and unbroken, and a
magnetic inspection to detect alloy-steel
fasteners, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2312, Revision 1,
dated April 29, 2004.
(2) For all airplanes: Before the initial
inspection threshold specified in Section
1.E., Table 1, of Boeing Alert Service Bulletin
747–57A2312, Revision 1, dated April 29,
2004; or within 18 months after the effective
date of this AD; whichever is later; perform
detailed and magnetic inspections, as
applicable, to detect A286 fasteners in the
diagonal brace underwing fitting at the
Number 1 and Number 4 engine pylons, as
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12:58 Jul 08, 2005
Jkt 205001
specified in Part 1 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2312, Revision 1, dated April 29,
2004. For the purposes of this AD, an A286
fastener is any fastener to which the magnet
is not attracted, and which cannot be
conclusively determined to be BACB30NX
(TI material) or BACB30US (Inconel material)
fasteners.
Ultrasonic Inspection for Damage
(i) For all alloy-steel or A286 fasteners
identified during the inspections in
accordance with paragraph (h) of this AD:
Before further flight, perform an ultrasonic
inspection for damage (including, but not
limited to, cracking or corrosion) of each
alloy-steel and A286 fastener, in accordance
with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–57A2312, Revision 1, dated April 29,
2004. If any bolt is missing or found damaged
during the inspection required by this
paragraph: Before further flight, perform an
ultrasonic inspection for damage of all 10
subject fasteners, in accordance with Part 2
of the Accomplishment Instructions of the
service bulletin. Doing the actions required
by this paragraph within the compliance time
specified in paragraph (f) of this AD
eliminates the need to do paragraph (f) of this
AD.
Undamaged Fastener: Repetitive Inspections
or No Further Action
(j) For any fastener that is found to be
installed and undamaged during the
inspections required by paragraph (i) of this
AD, do paragraph (j)(1), (j)(2), or (j)(3) of this
AD, as applicable.
(1) If no damage is found during the
inspections required by paragraph (i) of this
AD, and all 10 fasteners in the diagonal brace
underwing fitting at the Number 1 and
Number 4 engine pylons are either
BACB30NX or BACB30US fasteners: No
further action is required by this AD, though
the restrictions of paragraph (n) of this AD,
‘‘Parts Installation,’’ apply.
(2) For any undamaged alloy steel fastener:
Repeat the ultrasonic inspection specified in
paragraph (i) of this AD at intervals not to
exceed 18 months, until the actions in
paragraph (m) of this AD are done.
(3) For any undamaged A286 fastener:
Repeat the ultrasonic inspection specified in
paragraph (i) of this AD at intervals not to
exceed 8,000 flight cycles, until the actions
in paragraph (m) of this AD are done.
Repetitive Ultrasonic Inspections and
Corrective Actions
(k) For any missing or damaged fastener
found during the inspections required by
paragraph (i) or (j) of this AD: Before further
flight, install a new, improved fastener in any
location where a fastener is missing, and
replace any damaged fastener with a new,
improved fastener, in accordance with Part 3
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–57A2312,
Revision 1, dated April 29, 2004. Do an openhole HFEC inspection for cracking, corrosion,
or damage before installing the new fastener.
If any cracking, corrosion, or damage is
found: Before further flight, perform
applicable corrective actions in accordance
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with the service bulletin, except as provided
by paragraph (l) of this AD.
Repair
(l) If any damage (including but not limited
to cracking or corrosion) of the bolt hole that
exceeds the limits specified in Boeing Alert
Service Bulletin 747–57A2312, Revision 1,
dated April 29, 2004, is found during any
inspection required by this AD, and the
service bulletin specifies to contact Boeing
for appropriate action: Before further flight,
repair per a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA; or according to data meeting the
certification basis of the airplane approved
by an Authorized Representative for the
Boeing Delegation Option Authorization
Organization who the Manager, Seattle ACO,
has authorized to make this finding. For a
repair method to be approved by the
Manager, Seattle ACO, as required by this
paragraph, the Manager’s approval letter
must specifically reference this AD.
Optional Terminating Action
(m) Replacement of all alloy steel and
A286 fasteners with new, improved fasteners
in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–57A2312, Revision 1,
dated April 29, 2004 (including performing
an open-hole eddy current inspection for
cracking of the fastener holes and repairing,
as applicable), constitutes terminating action
for the repetitive inspection requirements of
this AD.
Parts Installation
(n) For Boeing Model 747–100, 747–200,
747–300, and 747SP series airplanes
equipped with titanium diagonal brace
underwing fittings, as identified in Boeing
Alert Service Bulletin 747–57A2312, dated
June 15, 2000: As of August 1, 2001, no
person may install, on any airplane, a
fastener having part number (P/N)
BACB30PE() * (); or any other fastener made
of 4340, 8740, PH13–8 Mo, or H–11 steel; in
the locations specified in this AD.
(o) Except as provided by paragraph (n) of
this AD, as of the effective date of this AD
no person may install, on any airplane, a
fastener having P/N BACB30PE() * (); or any
other fastener made of 4340, 8740, PH13–8
Mo, A286, or H–11 steel; in the locations
specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(p)(1) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) 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
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.
(3) AMOCs approved previously according
to AD 2001–13–06, amendment 39–12286 (66
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Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations
FR 34094, June 27, 2001), are approved as
AMOCs for the inspection requirements of
this AD only at fastener locations where the
AMOC provided for installing either
BACB30NX or BACB30US fasteners.
Material Incorporated by Reference
(q) You must use Boeing Alert Service
Bulletin 747–57A2312, dated June 15, 2000;
or Boeing Alert Service Bulletin 747–
57A2312, Revision 1, dated April 29, 2004;
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approves the incorporation by reference of
Boeing Alert Service Bulletin 747–57A2312,
Revision 1, dated April 29, 2004, in
accordance with 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
747–57A2312, dated June 15, 2000, as of
August 1, 2001 (66 FR 34094, June 27, 2001).
(3) To get copies of the service information,
contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207.
To view the AD docket, go to the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC. To review copies of the service
information, go to 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 https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on June 29,
2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–13432 Filed 7–8–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19679; Directorate
Identifier 2003–NM–132–AD; Amendment
39–14184; AD 2005–14–07]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 727, 727C, 727–100, 727–100C,
727–200, and 727–200F Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 727, 727C, 727–100, 727–
100C, 727–200, and 727–200F series
VerDate jul<14>2003
12:58 Jul 08, 2005
Jkt 205001
airplanes. This AD requires repetitive
inspections of the carriage attach fittings
on the foreflaps of each wing for
cracking and other discrepancies, and
corrective actions if necessary. For
certain airplanes, this AD also
concurrently requires various other
actions related to the subject area. This
AD also provides for an optional
terminating action for the repetitive
inspection requirements and for an
optional replacement that defers the
repetitive inspections. This AD is
prompted by reports of damaged or
failed outboard foreflaps with a cracked
or failed carriage attach fitting of the
foreflap sequencing carriage. We are
issuing this AD to detect and correct
fatigue cracking of the attach fittings of
the foreflap carriage of the wings, which
could result in partial or complete loss
of the foreflap and consequent loss of
controllability of the airplane.
DATES: This AD becomes effective
August 15, 2005.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of August 15, 2005.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the AD
docket on the Internet at https://
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 U.S. Department of Transportation,
400 Seventh Street, SW., room PL–401,
Washington, DC. This docket number is
FAA–2004–19679; the directorate
identifier for this docket is 2003–NM–
132–AD.
FOR FURTHER INFORMATION CONTACT:
Daniel F. Kutz; Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6456; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Boeing Model 727,
727C, 727–100, 727–100C, 727–200, and
727–200F series airplanes. That action,
published in the Federal Register on
November 24, 2004 (69 FR 68274),
proposed to require repetitive
inspections of the carriage attach fittings
on the foreflaps of each wing for
cracking and other discrepancies, and
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39647
corrective actions if necessary. For
certain airplanes, that action also
proposed to concurrently require
various other actions related to the
subject area. That action also proposed
an optional terminating action for the
repetitive inspection requirements and
an optional replacement that defers the
repetitive inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
Support for Proposed AD
One commenter, the airplane
manufacturer, supports the proposed
AD.
Request To Revise Applicability
One commenter requests that the
applicability of the proposed AD refer to
serial numbers (S/N) of the foreflap
assembly rather than to the S/Ns of the
affected airplanes. The commenter
states that flight controls are often
swapped from airplane to airplane to
accommodate maintenance and
overhaul requirements. The commenter
believes that tracking the S/N of the
foreflap assembly will ensure that all
affected parts (including spares) are
modified, reworked, or replaced.
We do not agree. The foreflap
assembly is part of the type design for
the affected Model 727 airplanes. Our
general policy is that, when an unsafe
condition has been identified, the AD is
issued so that it is applicable to the
type-certificated airplane, not to an item
that is part of the type design. Making
the AD applicable to the airplane model
ensures that operators of those airplanes
will be notified directly of the unsafe
condition and the action required to
correct it. While it is assumed that an
operator will know the models of
airplanes that it operates, there is a
potential that the operator will not
know or be aware of specific items, such
as a foreflap assembly, that are installed
on its airplanes. Therefore, calling out
the airplane model as the subject of the
AD prevents ‘‘unknowing noncompliance’’ on the part of the operator.
We have made no change in this regard
to the AD.
Request To Extend Compliance Time
One commenter requests that the
compliance time specified in paragraph
(h) of the proposed AD be revised from
3,500 flight cycles to 4,500 flight cycles.
The commenter states that the
modification instructions in paragraph
G. of Part II of the Accomplishment
E:\FR\FM\11JYR1.SGM
11JYR1
]]>Agencies
[Federal Register Volume 70, Number 131 (Monday, July 11, 2005)]
[Rules and Regulations]
[Pages 39644-39647]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-13432]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20243; Directorate Identifier 2004-NM-153-AD;
Amendment 39-14185; AD 2005-14-08]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 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 747-100, -200, -300, and
747SP series airplanes. That AD currently requires certain inspections
to find missing or alloy-steel taperlock fasteners (bolts) in the
diagonal brace underwing fittings, and corrective actions if necessary.
For airplanes with missing or alloy-steel fasteners, that AD also
mandates replacement of certain fasteners with new fasteners, which
constitutes terminating action for certain inspections. This new AD
expands the applicability to include additional airplane models and
requires a new inspection to determine fastener material and to find
missing or broken fasteners, and related investigative/corrective
actions if necessary. This AD is prompted by reports indicating that
cracked fasteners made of A286 material were found on airplanes that
had only fasteners made of A286 material installed in the area common
to the diagonal brace underwing fittings. We are issuing this AD to
prevent loss of the underwing fitting load path due to missing or
damaged alloy-steel or A286 taperlock fasteners, which could result in
separation of the engine and strut from the airplane.
DATES: This AD becomes effective August 15, 2005.
The incorporation by reference of Boeing Alert Service Bulletin
747-57A2312, Revision 1, dated April 29, 2004, is approved by the
Director of the Federal Register as of August 15, 2005.
On August 1, 2001 (66 FR 34094, June 27, 2001), the Director of the
Federal Register approved the incorporation by reference of Boeing
Alert Service Bulletin 747-57A2312, dated June 15, 2000.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the AD docket on the Internet at
https://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 U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Washington, DC. This docket number is FAA-2005-20243; the directorate
identifier for this docket is 2004-NM-153-AD.
FOR FURTHER INFORMATION CONTACT: Nicholas Kusz, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6432; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) with an AD to supersede
AD 2001-13-06, amendment 39-12286 (66 FR 34094, June 27, 2001). The
existing AD applies to certain Boeing Model 747-100, -200, -300, and
747SP series airplanes. The proposed AD was published in the Federal
Register on February 1, 2005 (70 FR 5066), to continue to require the
actions required by the existing AD. The proposed AD would also expand
the applicability to include additional airplane models and would
require a new inspection to determine fastener material and to find
missing or broken fasteners, and related investigative/corrective
actions if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD.
Support for the Proposed AD
One commenter supports the proposed AD.
Request To Increase Initial Inspection Threshold
One commenter requests that we revise paragraph (h)(1) of the
proposed AD to increase the initial inspection threshold from 12 months
to 18 months after the effective date of the AD for the inspection in
that paragraph. The commenter states that this would allow the
inspection to be performed during a regularly scheduled C-check.
We agree. Our intent was that the affected fasteners be inspected
during a regularly scheduled maintenance visit in which time permits
the fuel tank to be opened. We have revised paragraph (h)(1) of this AD
to specify a compliance threshold of 18 months after the effective date
of the AD.
Request To Clarify Subject Fasteners
One commenter requests that we revise paragraph (h) to clarify that
the inspections required by that paragraph apply to the aft-most 10
fasteners in the diagonal brace underwing fitting, not ``all fasteners
in the diagonal brace underwing fitting,'' as stated in the proposed
AD. We agree and have revised paragraph (h) of this AD accordingly.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, 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
There are about 739 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD, at an average labor rate of $65
per work hour.
[[Page 39645]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Cost per U.S.-
Action Work hours Parts airplane registered Fleet cost
airplanes
----------------------------------------------------------------------------------------------------------------
Detailed and magnetic inspection 2 None..................... $130 60 $7,800
(required by AD 2001-13-06).
Detailed and magnetic inspections 3 None..................... 195 140 27,300
(new requirement).
----------------------------------------------------------------------------------------------------------------
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. 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 FAA amends Sec. 39.13 by removing amendment 39-12286 (66 FR
34094, June 27, 2001) and by adding the following new airworthiness
directive (AD):
2005-14-08 Boeing: Amendment 39-14185. Docket No. FAA-2005-20243;
Directorate Identifier 2004-NM-153-AD.
Effective Date
(a) This AD becomes effective August 15, 2005.
Affected ADs
(b) This AD supersedes AD 2001-13-06, amendment 39-12286.
Applicability
(c) This AD applies to Model 747-100, 747-100B, 747-100B SUD,
747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F,
747SR, and 747SP series airplanes; certificated in any category; as
identified in Boeing Alert Service Bulletin 747-57A2312, Revision 1,
dated April 29, 2004.
Unsafe Condition
(d) This AD was prompted by reports indicating that cracked
fasteners made of A286 material were found on airplanes that had
only fasteners made of A286 material installed in the area common to
the diagonal brace underwing fittings. We are issuing this AD to
prevent loss of the underwing fitting load path due to missing or
damaged alloy-steel or A286 taperlock fasteners, which could result
in separation of the engine and strut from 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 2001-13-06
Repetitive Inspections
(f) For Boeing Model 747-100, 747-200, 747-300, and 747SP series
airplanes equipped with titanium diagonal brace underwing fittings,
as identified in Boeing Alert Service Bulletin 747-57A2312, dated
June 15, 2000: Within 12 months after August 1, 2001 (the effective
date of AD 2001-13-06, amendment 39-12286), do a one-time detailed
inspection of the diagonal brace underwing fitting at the Number 1
and Number 4 engine pylons to find missing taperlock fasteners
(bolts), and a magnetic inspection to find alloy-steel fasteners per
Part 1 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-57A2312, dated June 15, 2000; or Revision 1, dated
April 29, 2004.
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.''
(1) If no alloy-steel fasteners are found and no fasteners are
missing, no further action is required by this paragraph.
(2) If any alloy-steel fasteners are found or any fasteners are
missing, before further flight, do an ultrasonic inspection of the
alloy-steel fasteners to find damage per Part 2 of the
Accomplishment Instructions of the service bulletin.
(i) If no damaged alloy-steel fasteners are found, and no
fasteners are missing: Repeat the ultrasonic inspection thereafter
at intervals not to exceed 18 months until accomplishment of the
terminating action required by paragraph (g) of this AD.
(ii) If any damaged alloy-steel fasteners are found, or any
fasteners are missing: Before further flight, do an ultrasonic
inspection of all 10 aft fasteners (including non-alloy steel) per
Part 2 of the Accomplishment Instructions of the service bulletin.
Before further flight, replace damaged and missing fasteners with
new fasteners per Part 3 of the Accomplishment Instructions of the
service bulletin, except as provided by paragraph (l) of this AD.
Thereafter, repeat the inspection of the remaining alloy-steel
fasteners at intervals not to exceed 18 months until accomplishment
of the terminating action required by paragraph (g) or the optional
terminating action specified in paragraph (m) of this AD.
[[Page 39646]]
Terminating Action
(g) For Boeing Model 747-100, 747-200, 747-300, and 747SP series
airplanes equipped with titanium diagonal brace underwing fittings,
as identified in Boeing Alert Service Bulletin 747-57A2312, dated
June 15, 2000: Within 48 months after August 1, 2001, do the actions
required by paragraphs (g)(1) and (g)(2), or (g)(3) of this AD, per
Boeing Alert Service Bulletin 747-57A2312, dated June 15, 2000; or
Revision 1, dated April 29, 2004. Accomplishment of the actions
specified in this paragraph constitutes terminating action for the
repetitive inspection requirements of paragraph (f) of this AD.
(1) Perform an open-hole high frequency eddy current (HFEC)
inspection to detect cracks, corrosion, or damage at the bolt hole
locations of the aft 10 taperlock fasteners in the diagonal brace
underwing fitting at the Number 1 and Number 4 engine pylons per
Part 3 of the Accomplishment Instructions of the service bulletin.
If any cracking is detected, before further flight, perform
applicable corrective actions per the service bulletin, except as
provided by paragraph (l) of this AD.
(2) Before further flight: Replace all 10 aft taperlock
fasteners with new, improved fasteners per Part 3 of the
Accomplishment Instructions of the service bulletin.
(3) Do an ultrasonic inspection to find damaged fasteners per
Part 2 of the Accomplishment Instructions of the service bulletin.
Before further flight, replace all damaged non-alloy steel and all
alloy-steel fasteners with new fasteners per Part 3 of the
Accomplishment Instructions of the service bulletin. Do an open-hole
HFEC inspection before installation of the new fasteners; if any
cracking, corrosion, or damage is found, before further flight,
perform applicable corrective actions per the service bulletin,
except as provided by paragraph (l) of this AD.
New Requirements of This AD
Inspection for Missing/Broken Fasteners and to Determine Material
Type
(h) For the aft 10 taperlock fasteners in the diagonal brace
underwing fitting at the Number 1 and Number 4 engine pylons:
Perform the inspections in paragraphs (h)(1) and (h)(2) of this AD,
as applicable.
(1) For airplanes not identified in paragraph (f) of this AD:
Within 18 months after the effective date of this AD, perform a
detailed inspection to ensure that all fasteners are installed and
unbroken, and a magnetic inspection to detect alloy-steel fasteners,
in accordance with Part 1 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-57A2312, Revision 1, dated April
29, 2004.
(2) For all airplanes: Before the initial inspection threshold
specified in Section 1.E., Table 1, of Boeing Alert Service Bulletin
747-57A2312, Revision 1, dated April 29, 2004; or within 18 months
after the effective date of this AD; whichever is later; perform
detailed and magnetic inspections, as applicable, to detect A286
fasteners in the diagonal brace underwing fitting at the Number 1
and Number 4 engine pylons, as specified in Part 1 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2312, Revision 1, dated April 29, 2004. For the purposes of this
AD, an A286 fastener is any fastener to which the magnet is not
attracted, and which cannot be conclusively determined to be
BACB30NX (TI material) or BACB30US (Inconel material) fasteners.
Ultrasonic Inspection for Damage
(i) For all alloy-steel or A286 fasteners identified during the
inspections in accordance with paragraph (h) of this AD: Before
further flight, perform an ultrasonic inspection for damage
(including, but not limited to, cracking or corrosion) of each
alloy-steel and A286 fastener, in accordance with Part 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2312, Revision 1, dated April 29, 2004. If any bolt is missing or
found damaged during the inspection required by this paragraph:
Before further flight, perform an ultrasonic inspection for damage
of all 10 subject fasteners, in accordance with Part 2 of the
Accomplishment Instructions of the service bulletin. Doing the
actions required by this paragraph within the compliance time
specified in paragraph (f) of this AD eliminates the need to do
paragraph (f) of this AD.
Undamaged Fastener: Repetitive Inspections or No Further Action
(j) For any fastener that is found to be installed and undamaged
during the inspections required by paragraph (i) of this AD, do
paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable.
(1) If no damage is found during the inspections required by
paragraph (i) of this AD, and all 10 fasteners in the diagonal brace
underwing fitting at the Number 1 and Number 4 engine pylons are
either BACB30NX or BACB30US fasteners: No further action is required
by this AD, though the restrictions of paragraph (n) of this AD,
``Parts Installation,'' apply.
(2) For any undamaged alloy steel fastener: Repeat the
ultrasonic inspection specified in paragraph (i) of this AD at
intervals not to exceed 18 months, until the actions in paragraph
(m) of this AD are done.
(3) For any undamaged A286 fastener: Repeat the ultrasonic
inspection specified in paragraph (i) of this AD at intervals not to
exceed 8,000 flight cycles, until the actions in paragraph (m) of
this AD are done.
Repetitive Ultrasonic Inspections and Corrective Actions
(k) For any missing or damaged fastener found during the
inspections required by paragraph (i) or (j) of this AD: Before
further flight, install a new, improved fastener in any location
where a fastener is missing, and replace any damaged fastener with a
new, improved fastener, in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2312, Revision 1, dated April 29, 2004. Do an open-hole HFEC
inspection for cracking, corrosion, or damage before installing the
new fastener. If any cracking, corrosion, or damage is found: Before
further flight, perform applicable corrective actions in accordance
with the service bulletin, except as provided by paragraph (l) of
this AD.
Repair
(l) If any damage (including but not limited to cracking or
corrosion) of the bolt hole that exceeds the limits specified in
Boeing Alert Service Bulletin 747-57A2312, Revision 1, dated April
29, 2004, is found during any inspection required by this AD, and
the service bulletin specifies to contact Boeing for appropriate
action: Before further flight, repair per a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA; or
according to data meeting the certification basis of the airplane
approved by an Authorized Representative for the Boeing Delegation
Option Authorization Organization who the Manager, Seattle ACO, has
authorized to make this finding. For a repair method to be approved
by the Manager, Seattle ACO, as required by this paragraph, the
Manager's approval letter must specifically reference this AD.
Optional Terminating Action
(m) Replacement of all alloy steel and A286 fasteners with new,
improved fasteners in accordance with Part 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2312, Revision
1, dated April 29, 2004 (including performing an open-hole eddy
current inspection for cracking of the fastener holes and repairing,
as applicable), constitutes terminating action for the repetitive
inspection requirements of this AD.
Parts Installation
(n) For Boeing Model 747-100, 747-200, 747-300, and 747SP series
airplanes equipped with titanium diagonal brace underwing fittings,
as identified in Boeing Alert Service Bulletin 747-57A2312, dated
June 15, 2000: As of August 1, 2001, no person may install, on any
airplane, a fastener having part number (P/N) BACB30PE() * (); or
any other fastener made of 4340, 8740, PH13-8 Mo, or H-11 steel; in
the locations specified in this AD.
(o) Except as provided by paragraph (n) of this AD, as of the
effective date of this AD no person may install, on any airplane, a
fastener having P/N BACB30PE() * (); or any other fastener made of
4340, 8740, PH13-8 Mo, A286, or H-11 steel; in the locations
specified in this AD.
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, Seattle ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) 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 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.
(3) AMOCs approved previously according to AD 2001-13-06,
amendment 39-12286 (66
[[Page 39647]]
FR 34094, June 27, 2001), are approved as AMOCs for the inspection
requirements of this AD only at fastener locations where the AMOC
provided for installing either BACB30NX or BACB30US fasteners.
Material Incorporated by Reference
(q) You must use Boeing Alert Service Bulletin 747-57A2312,
dated June 15, 2000; or Boeing Alert Service Bulletin 747-57A2312,
Revision 1, dated April 29, 2004; to perform the actions that are
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approves the
incorporation by reference of Boeing Alert Service Bulletin 747-
57A2312, Revision 1, dated April 29, 2004, in accordance with 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-
57A2312, dated June 15, 2000, as of August 1, 2001 (66 FR 34094,
June 27, 2001).
(3) To get copies of the service information, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
To view the AD docket, go to the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Nassif Building, Washington, DC. To review copies of the service
information, go to 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 https://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html.
Issued in Renton, Washington, on June 29, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-13432 Filed 7-8-05; 8:45 am]
BILLING CODE 4910-13-P
