[Federal Register: February 1, 2005 (Volume 70, Number 20)]
[Proposed Rules]
[Page 5066-5070]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01fe05-15]
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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]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Boeing Model 747-100, -200, -
300, and 747SP series airplanes. The existing 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, the existing AD also mandates replacement of certain
fasteners with new fasteners, which constitutes terminating action for
certain inspections. This proposed AD would 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. This
proposed 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 proposing 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: We must receive comments on this proposed AD by March 18, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web Site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide Rulemaking Web Site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
You can examine the contents of this 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., room PL-401,
on the plaza level of the Nassif Building, 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:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-20243;
Directorate Identifier 2004-NM-153-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
Examining the Docket
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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
On June 19, 2001, we issued AD 2001-13-06, amendment 39-12286 (66
FR 34094, June 27, 2001), for certain Boeing Model 747-100, -200, -300,
and 747SP series airplanes. That AD 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 the repetitive inspection. That AD was prompted
by a report indicating that broken taperlock fasteners (bolts) were
found on the diagonal brace underwing fittings on the outboard strut at
the Number 1 and Number 4 engine pylons on a Boeing Model 747-200
series airplane having titanium underwing fittings. We issued that AD
to prevent loss of the underwing fitting load path due to missing or
damaged alloy-steel taperlock fasteners, which could result in
separation of the engine and strut from the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2001-13-06, we have received reports indicating
that fractured fasteners have been found on Model 747-200B series
airplanes that weren't included in the applicability of the existing
AD. The fractured fasteners were made of A286 material, and only
fasteners made of that material were installed in the diagonal brace
underwing fitting. (After this, this proposed AD refers to fasteners
made of A286 material as ``A286 fasteners.'') Previously, cracked or
broken A286 fasteners were found only on airplanes that had a
combination of alloy-steel and A286 fasteners. Thus, these previous
incidents were attributed to overload of the A286 fasteners due to
[[Page 5067]]
fracture of adjacent alloy-steel bolts. Fractured alloy-steel or A286
fasteners could lead to loss of the underwing fitting load path, which
could result in separation of the engine and strut from the airplane.
Alloy-steel or A286 fasteners may be installed in the diagonal
brace underwing fitting on certain Boeing 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. Therefore, all of these
models and series may be subject to the unsafe condition revealed on
the Boeing Model 747-200B series airplanes.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-57A2312,
Revision 1, dated April 29, 2004. The service bulletin describes
procedures for performing the following actions for the fasteners in
the diagonal brace underwing fittings:
A general visual inspection to ensure that all fasteners
are installed and unbroken.
A magnetic inspection to determine fastener material.
If any alloy-steel or A286 fastener is found, repetitive
ultrasonic inspections for damage of all 10 aft fasteners (regardless
of material).
Replacement of damaged fasteners with new, improved
fasteners (including an open-hole eddy current inspection for cracking
of the fastener holes, and repair if necessary).
Replacement of all alloy steel and A286 fasteners with
new, improved fasteners (including an open-hole eddy current inspection
for cracking of the fastener holes, and repair if necessary), which
eliminates the need for the repetitive inspections.
If any damage is found that exceeds certain limits, the service
bulletin recommends contacting Boeing for appropriate action.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. This proposed AD would supersede AD 2001-13-
06. This proposed AD would retain the requirements of the existing AD.
This proposed AD would also expand the applicability of the existing AD
and require accomplishing the actions specified in the service bulletin
described previously, except as discussed under ``Differences Between
the Proposed AD and Service Bulletin.''
Differences Between the Proposed AD and Service Bulletin
The service bulletin specifies a magnetic inspection to detect
alloy-steel fasteners. We find that a detailed inspection is also
necessary to detect A286 fasteners. 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 have a part number that
begins with BACB30NX (fasteners of T1 material) or BACB30US (fasteners
of Inconel material). This difference has been coordinated with the
airplane manufacturer, and it agrees with our determination. If Boeing
Alert Service Bulletin 747-57A2312 is revised in the future, the new
revision will take into account the proposed requirements of this AD.
If any A286 fastener is found during the inspection to determine
material type, the service bulletin specifies that you must do an
ultrasonic inspection for damage of all 10 aft fasteners in the
diagonal brace underwing fitting. However, this proposed AD would
require you to perform an ultrasonic inspection for damage of only
alloy-steel and A286 fasteners, unless a cracked (or otherwise damaged)
fastener is found. If a cracked or otherwise damaged fastener is found,
this proposed AD would require ultrasonic inspection for damage of all
10 aft fasteners. This difference has been coordinated with the
airplane manufacturer, and it agrees with our determination. If Boeing
Alert Service Bulletin 747-57A2312 is revised in the future, the new
revision will take into account the proposed requirements of this AD.
Figure 1 of the service bulletin recommends that you perform a
general visual inspection to ensure that all fasteners are installed
and unbroken. We have determined that the procedures needed for this
inspection constitute a detailed inspection. Note 1 of this AD defines
a detailed inspection. This difference has been coordinated with the
airplane manufacturer, and it agrees with our determination. If Boeing
Alert Service Bulletin 747-57A2312 is revised in the future, the new
revision will take into account the proposed requirements of this AD.
Section 1.E., Table 1, of the service bulletin specifies an initial
inspection threshold of between 11,000 and 29,000 total flight cycles
for the inspection to detect A286 fasteners. Section 1.E. of the
service bulletin also specifies a grace period of 18 months after the
issue date of Revision 1 of the service bulletin. This proposed AD
would require compliance prior to the threshold specified in the
service bulletin, or within 18 months after the effective date of the
AD, whichever occurs later.
The service bulletin specifies that you may contact the
manufacturer for instructions on how to repair certain conditions, but
this proposed AD would require you to repair those conditions in one of
the following ways:
Using a method that the Manager of the Seattle Aircraft
Certification Office approves; or
Using data that meet the certification basis of the
airplane that have been approved by an Authorized Representative for
the Boeing Delegation Option Authorization Organization who has been
authorized by the FAA to make those findings.
Changes to Existing AD
This proposed AD would retain all requirements of AD 2001-13-06.
Since AD 2001-13-06 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
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Corresponding requirement
Requirement in AD 2001-13-06 in this proposed AD
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Paragraph (a)............................. Paragraph (f).
Paragraph (b)............................. Paragraph (g).
Paragraph (c)............................. Paragraph (l).
Paragraph (d)............................. Paragraph (n).
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Also, we have changed all references to a ``detailed visual
inspection'' in the existing AD to ``detailed inspection'' in this
action. Note 1 defines a ``detailed inspection.''
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 proposed AD, at an average labor
rate of $65 per work hour.
[[Page 5068]]
Estimated Costs
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Number of U.S.-
Action Work hours Parts Cost per registered Fleet cost
airplane airplanes
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Detailed and magnetic 2 None............ $130 60 $7,800
inspection (required by AD
2001-13-06).
Detailed and magnetic 3 None............ 195 140 27,300
inspections (new proposed
action).
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Authority for This Rulemaking
The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the United States Code. 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.
This rulemaking is promulgated under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, the FAA is charged 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 AD.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing amendment 39-12286 (66 FR
34094, June 27, 2001) and adding the following new airworthiness
directive (AD):
Boeing: Docket No. FAA-2005-20243; Directorate Identifier 2004-NM-
153-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this airworthiness directive (AD) action by March 18, 2005.
Affected ADs
(b) This AD supersedes AD 2001-13-06, amendment 39-12286 (66 FR
34094, June 27, 2001).
Applicability:
(c) This AD applies to Model 747-100, 747-100B, 747-100B SUD, -
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 5069]]
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 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 all 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 12 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 (T1 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 ACO, 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 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 part number 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 5070]]
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.
Issued in Renton, Washington, on January 21, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-1794 Filed 1-31-05; 8:45 am]
BILLING CODE 4910-13-P