[Federal Register: July 11, 2005 (Volume 70, Number 131)]
[Rules and Regulations]
[Page 39644-39647]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11jy05-3]
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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.
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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
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 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
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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).
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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. 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 http://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]
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