[Federal Register Volume 65, Number 118 (Monday, June 19, 2000)]
[Rules and Regulations]
[Pages 37848-37851]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-15181]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-78-AD; Amendment 39-11794; AD 2000-12-16]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Boeing Model 747 series airplanes, that 
currently requires repetitive inspections to detect fatigue cracking or 
loose or missing fasteners of the aft torque bulkheads of the outboard 
nacelle struts; and repair, if necessary. This amendment expands the 
applicability of the existing AD to include certain additional 
airplanes, and removes certain other airplanes from the applicability 
of the existing AD. For all airplanes subject to this AD, this 
amendment also requires accomplishment of a new terminating action. 
This action is necessary to prevent fatigue cracking and loose or 
missing fasteners in the aft torque bulkheads of the outboard nacelle 
struts, which could result in failure of an outboard nacelle strut 
diagonal brace load path and possible separation of the nacelle from 
the wing. This action is intended to address the identified unsafe 
condition.

DATES: Effective July 5, 2000.
    The incorporation by reference of Boeing Alert Service Bulletin 
747-54A2184, Revision 1, dated May 6, 1999, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
July 5, 2000.
    The incorporation by reference of Boeing Alert Service Bulletin 
747-54A2184, dated July 3, 1997, as listed in the regulations, was 
approved previously by the Director of the Federal Register as of March 
18, 1999 (64 FR 10205, March 3, 1999).
    Comments for inclusion in the Rules Docket must be received on or 
before August 18, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-78-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays. Comments may also be sent via the Internet using the 
following address: <a href="/cdn-cgi/l/email-protection#536a7e323d3e7e3a3221303c3e3e363d27133532327d343c25"><span class="__cf_email__" data-cfemail="89b0a4e8e7e4a4e0e8fbeae6e4e4ece7fdc9efe8e8a7eee6ff">[email protected]</span></a>. Comments sent via the 
Internet must contain ``Docket No. 2000-NM-78-AD'' in the subject line 
and need not be submitted in triplicate.
    The service information referenced in this AD may be obtained from 
Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 
98124-2207. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tamara L. Anderson, Aerospace 
Engineer, Airframe Branch, ANM-120S, FAA, Transport Airplane 
Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue, 
SW., Renton, Washington 98055-4056; telephone (425) 227-2771; fax (425) 
227-1181.

SUPPLEMENTARY INFORMATION: On February 22, 1999, the FAA issued AD 99-
05-06, amendment 39-11054 (64 FR 10205, March 3, 1999), applicable to 
certain Boeing Model 747 series airplanes, to require repetitive 
inspections to detect fatigue cracking or loose or missing fasteners of 
the aft torque bulkheads of the outboard nacelle struts; and repair, if 
necessary. That action was prompted by a report indicating that 
cracking was found in the aft torque bulkheads of the outboard nacelle 
struts, and by the availability of new service instructions for 
detecting fatigue cracking that would not have been detected by the 
required actions of the existing AD. The requirements of that AD are 
intended to detect and correct such fatigue cracking and loose or 
missing fasteners, which could result in failure of an outboard nacelle 
strut diagonal brace load path and possible separation of the nacelle 
from the wing.

Explanation of Relevant Service Information

    Since the issuance of AD 99-05-06, the FAA has reviewed and 
approved Boeing Alert Service Bulletin 747-54A2184, Revision 1, dated 
May 6, 1999. The alert service bulletin describes procedures for 
repetitive inspections to detect fatigue cracking or loose or missing 
fasteners of the aft torque bulkheads of the outboard nacelle struts; 
and repair, if necessary. These procedures are substantially similar to 
those described in Boeing Alert Service Bulletin 747-54A2184, dated 
July 3, 1997, which was referenced in AD 99-05-06 as an appropriate 
source of service information for accomplishment of certain 
requirements of that AD. However, Revision 1 of the alert service 
bulletin adds new airplanes (Group 5) that are subject to the 
repetitive inspections (and repair, if necessary) described in the 
original issue of the alert service bulletin and required by AD 99-05-
06. For certain airplanes (i.e., the airplanes listed in Groups 1, 2, 
and 5 of the alert service bulletin), the alert service bulletin also 
describes procedures for a terminating action that eliminates the need 
for the repetitive inspections described in the alert service bulletin 
for affected airplanes. The terminating action involves installation of 
doublers and fillers on the forward side of the lower spar fitting. 
Accomplishment of the actions specified in the alert service bulletin 
is

[[Page 37849]]

intended to adequately address the identified unsafe condition.

Explanation of Applicability of This AD

    For airplanes listed in Groups 3 and 4 of the original issue of 
Boeing Alert Service Bulletin 747-54A2184, paragraph (c) of AD 99-05-06 
describes a detailed visual inspection to detect fatigue cracking and 
loose or missing fasteners of the aft torque bulkheads of the number 1 
and number 4 nacelle struts. For these airplanes in Groups 3 and 4, 
paragraph (d) of AD 99-05-06 states, ``Accomplishment of the nacelle 
strut modifications required in AD 95-13-07, amendment 39-9287 [60 FR 
33336, June 28, 1995] * * * constitutes terminating action for the 
requirements of this AD.'' Paragraph (a) of AD 95-13-07 requires 
accomplishment of the nacelle strut modifications within 56 months 
after July 28, 1995 (the effective date of that AD). Considering that 
the compliance time for this modification has now passed, the FAA finds 
that it is unnecessary in this AD to continue to reference the 
inspection and terminating action for airplanes listed in Groups 3 and 
4 of the alert service bulletin. Therefore, paragraphs (c) and (d) of 
AD 99-05-06 have not been included in this AD, and the applicability 
statement of this AD has been revised to include only airplanes listed 
in Groups 1, 2, and 5 of Revision 1 of the alert service bulletin.

Explanation of Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, this AD 
supersedes AD 99-05-06 to continue to require repetitive inspections to 
detect fatigue cracking or loose or missing fasteners of the aft torque 
bulkheads of the outboard nacelle struts; and repair, if necessary. 
This AD expands the applicability of the existing AD to include certain 
additional airplanes, and removes certain other airplanes from the 
applicability of the existing AD. For all airplanes subject to this AD, 
this amendment also requires accomplishment of a new terminating 
action. The actions are required to be accomplished in accordance with 
the alert service bulletin described previously, except as discussed 
below.

Differences Between Alert Service Bulletin and This AD

    Operators should note that, although the alert service bulletin 
specifies that the manufacturer may be contacted for disposition of 
certain repair conditions, this AD requires the repair of those 
conditions to be accomplished in accordance with a method approved by 
the FAA, or in accordance with data meeting the type certification 
basis of the airplane approved by a Boeing Company Designated 
Engineering Representative who has been authorized by the FAA to make 
such findings.
    In addition, the FAA has determined that there is an error in Item 
3.A.5.c. under ``Part 4--Terminating Action'' in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-54A2184, Revision 1. 
The words, ``as shown by Figure 11,'' should read ``as shown by Figure 
12.'' ``Note 6'' has been included in this AD to clarify this error.

Cost Impact

    None of the Model 747 series airplanes affected by this action are 
on the U.S. Register. All airplanes included in the applicability of 
this rule currently are operated by non-U.S. operators under foreign 
registry; therefore, they are not directly affected by this AD action. 
However, the FAA considers that this rule is necessary to ensure that 
the unsafe condition is addressed in the event that any of these 
subject airplanes are imported and placed on the U.S. Register in the 
future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would take approximately 15 work hours to 
accomplish the required inspections, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of these 
inspections would be $900 per airplane.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would take approximately 45 work hours to 
accomplish the required terminating action, at an average labor rate of 
$60 per work hour. Required parts would cost approximately $8,166 per 
airplane. Based on these figures, the cost impact of the required 
terminating action on U.S. operators would be $10,866 per airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
rule by submitting such written data, views, or arguments as they may 
desire. Communications shall identify the Rules Docket number and be 
submitted in triplicate to the address specified under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Submit comments using the following format:
    <bullet> Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-78-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44

[[Page 37850]]

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. A final 
evaluation has been prepared for this action and it is contained in the 
Rules Docket. A copy of it may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by removing amendment 39-11054 (64 FR 
10205, March 3, 1999), and by adding a new airworthiness directive (AD) 
amendment 39-11794, to read as follows:

2000-12-16  Boeing: Amendment 39-11794. Docket 2000-NM-78-AD. 
Supersedes AD 99-05-06, Amendment 39-11054.

    Applicability: Model 747 series airplanes; as listed in Groups 
1, 2, and 5 of Boeing Alert Service Bulletin 747-54A2184, Revision 
1, dated May 6, 1999; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (f)(1) 
of this AD. The request should include an assessment of the effect 
of the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue cracking and loose or missing fasteners in 
the aft torque bulkheads of the outboard nacelle struts, which could 
result in failure of an outboard nacelle strut diagonal brace load 
path and possible separation of the nacelle from the wing, 
accomplish the following:

Restatement of Requirements of AD 99-05-06

Repetitive Detailed Visual Inspections and Repair: Groups 1 and 2

    (a) For airplanes identified as Groups 1 and 2 airplanes in 
Boeing Alert Service Bulletin 747-54A2184, dated July 3, 1997: Prior 
to the accumulation of 8,000 total flight cycles, or within 8,000 
flight cycles since modification in accordance with AD 95-13-05, 
amendment 39-9285, or within 30 days after March 18, 1999 (the 
effective date of AD 99-05-06, amendment 39-11054), whichever occurs 
latest, perform a detailed visual inspection of the aft torque 
bulkheads of the number 1 and number 4 nacelle struts to detect 
fatigue cracking and loose or missing fasteners. The inspection 
shall be accomplished in accordance with Part I of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2184, dated July 3, 1997, or Revision 1, dated May 6, 1999.

    Note 2: There is a typographical error on Sheet 3 of Figure 1 of 
Boeing Alert Service Bulletin 747-54A2184, dated July 3, 1997. The 
words ``Group 1 airplanes'' should read ``Groups 1 and 2 
airplanes.''

    (1) If no cracking, and no loose or missing fastener, is found, 
repeat the inspection thereafter at the intervals specified in 
Figure 1 of the alert service bulletin.
    (2) If any cracking, or any loose or missing fastener, is found, 
prior to further flight, repair in accordance with Part III of the 
alert service bulletin. Repeat the inspection thereafter at the 
intervals specified in Figure 1 of the alert service bulletin. Where 
the service bulletin specifies that the manufacturer may be 
contacted for disposition of certain repair conditions, repair in 
accordance with a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA, Transport Airplane Directorate; or 
in accordance with data meeting the type certification basis of the 
airplane approved by a Boeing Company designated engineering 
representative (DER) who has been authorized by the Manager, Seattle 
ACO, to make such findings. 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.

Repetitive NDT Inspections and Repair: Groups 1 and 2

    (b) For airplanes identified as Groups 1 and 2 airplanes in 
Boeing Alert Service Bulletin 747-54A2184, dated July 3, 1997: Prior 
to the accumulation of 8,000 total flight cycles, or within 8,000 
flight cycles since modification in accordance with AD 95-13-05, 
amendment 39-9285, or within 30 days after March 18, 1999, whichever 
occurs latest, perform a non-destructive test (NDT) inspection of 
the aft torque bulkheads of the number 1 and number 4 nacelle struts 
to detect fatigue cracking. The NDT inspection shall be accomplished 
in accordance with Part II of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-54A2184, dated July 3, 1997, or 
Revision 1, dated May 6, 1999.

    Note 3: The alert service bulletin refers to a variety of NDT 
inspections, consisting of ultrasonic inspections, surface eddy 
current inspections, and open-hole eddy current inspections. The 
logic diagram in Figure 1 of the alert service bulletin states the 
conditions under which each of these inspections is to be performed.

    (1) If no cracking is found, repeat the inspection thereafter at 
the intervals specified in Figure 1 of the alert service bulletin.
    (2) If any cracking is found, prior to further flight, repair in 
accordance with Part III of the alert service bulletin. Repeat the 
inspection thereafter at the intervals specified in Figure 1 of the 
alert service bulletin. Where the alert service bulletin specifies 
that the manufacturer may be contacted for disposition of certain 
repair conditions, repair in accordance with a method approved by 
the Manager, Seattle ACO; or in accordance with data meeting the 
type certification basis of the airplane approved by a Boeing 
Company DER who has been authorized by the Manager, Seattle ACO, to 
make such findings. 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.

New Requirements of This AD

    Note 4: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

Repetitive Detailed Visual Inspections and Repair: Group 5

    (c) For airplanes identified as Group 5 of Boeing Alert Service 
Bulletin 747-54A2184, Revision 1, dated May 6, 1999: Prior to the 
accumulation of 8,000 total flight cycles, or within 90 days after 
the effective date of this AD, whichever occurs later, perform a 
detailed visual inspection of the aft torque bulkheads of the number 
1 and number 4 nacelle struts to detect fatigue cracking and loose 
or missing fasteners. The inspection shall be accomplished in 
accordance with Part I of the Accomplishment Instructions of the 
alert service bulletin.
    (1) If no cracking, and no loose or missing fastener, is found, 
repeat the inspection thereafter at the intervals specified in 
Figure 1 of the alert service bulletin.
    (2) If any cracking, or any loose or missing fastener, is found, 
prior to further flight, repair in accordance with Part III of the 
alert service bulletin. Repeat the inspection thereafter at the 
intervals specified in Figure 1 of the alert service bulletin. Where 
the service bulletin specifies that the manufacturer may be 
contacted for disposition of certain repair conditions,

[[Page 37851]]

repair in accordance with a method approved by the Manager, Seattle 
ACO, FAA, Transport Airplane Directorate; or in accordance with data 
meeting the type certification basis of the airplane approved by a 
Boeing Company DER who has been authorized by the Manager, Seattle 
ACO, to make such findings. 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.

Repetitive NDT Inspections and Repair: Group 5

    (d) For airplanes identified as Group 5 airplanes in Boeing 
Alert Service Bulletin 747-54A2184, Revision 1, dated May 6, 1999: 
Prior to the accumulation of 8,000 total flight cycles, or within 90 
days after the effective date of this AD, whichever occurs later, 
perform an NDT inspection of the aft torque bulkheads of the number 
1 and number 4 nacelle struts to detect fatigue cracking. The NDT 
inspection shall be accomplished in accordance with Part II of the 
Accomplishment Instructions of the alert service bulletin.

    Note 5: The alert service bulletin refers to a variety of NDT 
inspections, consisting of ultrasonic inspections, surface eddy 
current inspections, and open-hole eddy current inspections. The 
logic diagram in Figure 1 of the alert service bulletin states the 
conditions under which each of these inspections is to be performed.

    (1) If no cracking is found, repeat the inspection thereafter at 
the intervals specified in Figure 1 of the alert service bulletin.
    (2) If any cracking is found, prior to further flight, repair in 
accordance with Part III of the alert service bulletin. Repeat the 
inspection thereafter at the intervals specified in Figure 1 of the 
alert service bulletin. Where the alert service bulletin specifies 
that the manufacturer may be contacted for disposition of certain 
repair conditions, repair in accordance with a method approved by 
the Manager, Seattle ACO; or in accordance with data meeting the 
type certification basis of the airplane approved by a Boeing 
Company DER who has been authorized by the Manager, Seattle ACO, to 
make such findings. 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.

Terminating Action: Groups 1, 2, and 5

    (e) For airplanes identified as Group 1, 2, and 5 airplanes in 
Boeing Alert Service Bulletin 747-54A2184, Revision 1, dated May 6, 
1999: At the time specified in paragraph (e)(1), (e)(2), or (e)(3), 
as applicable, accomplish the terminating action (installation of 
doublers and fillers on the forward side of the lower spar fitting) 
in accordance with the alert service bulletin. Accomplishment of 
this paragraph constitutes terminating action for the repetitive 
inspections required by this AD.

    Note 6: There is an error in Item 3.A.5.c. under ``Part 4--
Terminating Action'' in the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-54A2184, Revision 1. The words, ``as 
shown by Figure 11,'' should read ``as shown by Figure 12.''

    (1) For airplanes in Groups 1, 2, and 5 on which the interim 
repair described in Part 3 of the Accomplishment Instructions of the 
alert service bulletin has NOT been accomplished; and Groups 1 and 2 
airplanes on which the requirements of AD 95-13-05, amendment 39-
9285, have NOT been accomplished: Accomplish the terminating action 
prior to the accumulation of 8,000 total flight cycles or within 5 
years after the effective date of this AD, whichever occurs later.
    (2) For airplanes in Groups 1, 2, and 5 on which the interim 
repair described in Part 3 of the Accomplishment Instructions of the 
alert service bulletin HAS been accomplished: Accomplish the 
terminating action within 3,000 flight cycles after accomplishment 
of the interim repair, or within 18 months after the effective date 
of this AD, whichever occurs later.
    (3) For airplanes in Groups 1 and 2 on which the requirements of 
AD 95-13-05, amendment 39-9285, HAVE been accomplished: Accomplish 
the terminating action within 8,000 flight cycles after 
accomplishment of the requirements of AD 95-13-05, amendment 39-
9285, or within 5 years after the effective date of this AD, 
whichever occurs later.

Alternative Methods of Compliance

    (f)(1) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle ACO. Operators shall submit 
their requests through an appropriate FAA Principal Maintenance 
Inspector, who may add comments and then send it to the Manager, 
Seattle ACO.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 99-05-06, amendment 39-11054, are approved as 
alternative methods of compliance with this AD.

    Note 7: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (g) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be accomplished.

Incorporation by Reference

    (h) Except as provided in paragraphs (a)(2), (b)(2), (c)(2), and 
(d)(2) of this AD, the actions shall be done in accordance with 
Boeing Alert Service Bulletin 747-54A2184, dated July 3, 1997, or 
Boeing Alert Service Bulletin 747-54A2184, Revision 1, dated May 6, 
1999.
    (1) The incorporation by reference of Boeing Alert Service 
Bulletin 747-54A2184, Revision 1, dated May 6, 1999, is approved by 
the Director of the Federal Register, in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Boeing Alert Service 
Bulletin 747-54A2184, dated July 3, 1997, was approved previously by 
the Director of the Federal Register as of March 18, 1999 (64 FR 
10205, March 3, 1999).
    (3) Copies may be obtained from Boeing Commercial Airplane 
Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (i) This amendment becomes effective on July 5, 2000.

    Issued in Renton, Washington, on June 9, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-15181 Filed 6-16-00; 8:45 am]
BILLING CODE 4910-13-U


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