[Federal Register Volume 70, Number 20 (Tuesday, February 1, 2005)]
[Proposed Rules]
[Pages 5066-5070]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-1794]


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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.
    <bullet> DOT Docket Web Site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide Rulemaking Web Site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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:
    <bullet> A general visual inspection to ensure that all fasteners 
are installed and unbroken.
    <bullet> A magnetic inspection to determine fastener material.
    <bullet> If any alloy-steel or A286 fastener is found, repetitive 
ultrasonic inspections for damage of all 10 aft fasteners (regardless 
of material).
    <bullet> 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).
    <bullet> 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:
    <bullet> Using a method that the Manager of the Seattle Aircraft 
Certification Office approves; or
    <bullet> 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
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in AD 2001-13-06              in this proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  Paragraph (f).
Paragraph (b).............................  Paragraph (g).
Paragraph (c).............................  Paragraph (l).
Paragraph (d).............................  Paragraph (n).
------------------------------------------------------------------------

    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