[Federal Register Volume 70, Number 53 (Monday, March 21, 2005)]
[Rules and Regulations]
[Pages 13349-13353]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-5388]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19535; Directorate Identifier 2004-NM-78-AD; 
Amendment 39-14020; AD 2005-06-12]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-300, 747SP, and 747SR Series 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, 747-100B, 747-100B 
SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes. That AD 
currently requires one-time inspections for cracking in certain upper 
deck floor beams and follow-on actions. This new AD expands the 
existing inspection area and requires inspecting fastener holes in 
certain areas of airplanes modified previously, and taking corrective 
actions if necessary. This action also defines new sources for 
instructions for repairs and post-modification/repair inspections. This 
AD is prompted by reports of fatigue cracking of the upper chord of 
certain upper deck floor beams. We are issuing this AD to find and fix 
cracking in certain upper deck floor beams, which could extend and 
sever floor beams adjacent to the body frame and result in rapid 
depressurization and loss of controllability of the airplane.

DATES: This AD becomes effective April 25, 2005.
    The incorporation by reference of Boeing Service Bulletin 747-
53A2459, Revision 1, dated March 11, 2004, is approved by the Director 
of the Federal Register as of April 25, 2005.
    On October 16, 2002 (67 FR 57510, September 11, 2002), the Director 
of the Federal Register approved the incorporation by reference of 
Boeing Alert Service Bulletin 747-53A2459, dated January 11, 2001.

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-2004-19535; the directorate 
identifier for this docket is 2004-NM-78-AD.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437; 
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 2002-18-04, amendment 39-12878 (67 FR 57510, September 11, 2002). 
The existing AD applies to certain Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes. The 
proposed AD was published in the Federal Register on November 5, 2004 
(69 FR 64525), to continue to require one-time inspections for cracking 
in certain upper deck floor beams and follow-on actions. The proposed 
AD would expand the existing inspection area, and would require 
inspecting fastener holes in certain areas of airplanes modified 
previously, and taking corrective actions if necessary. The proposed AD 
also would define new sources for instructions for repairs and post-
modification/repair inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD by a single commenter.

Request To Revise Delegation Language

    The commenter requests that we revise the proposed AD to change 
references to approval of repairs or alternative methods of compliance 
(AMOCs) by Boeing Company Designated Engineering Representatives 
(DERs). The commenter states that these provisions should refer to 
approval by Authorized Representatives (ARs) of the Boeing Delegation 
Option Authorization (DOA) Organization. The commenter notes that, 
since the issuance of the proposed AD, Boeing has received a DOA.
    We concur. We have revised paragraphs (h)(1)(i), (h)(2), and (i) of 
this

[[Page 13350]]

AD (which are restated requirements of AD 2002-18-04) to delegate the 
authority to approve a repair to a Boeing Company DER or to an AR of 
the Boeing DOA Organization. We have revised paragraphs (m) and (o)(2) 
to delegate the authority to approve a repair or an AMOC to an AR of 
the Boeing DOA.

Request To Revise Note 2 to Acknowledge Terminating Action

    The commenter requests that we revise Note 2 of the proposed AD, 
which states:

    There is no terminating action at this time for the repetitive 
post-modification/repair inspections in accordance with paragraph 
(i) of this AD, and instructions for those inspections are not 
provided in the original issue of Boeing Alert Service Bulletin 747-
53A2459, dated January 11, 2001.

The commenter notes that paragraph (l) of the proposed AD states that 
doing the initial inspection required by that paragraph terminates the 
repetitive inspections required by paragraph (i).
    We agree. Note 2 was carried over with the other requirements of AD 
2002-18-04. We inadvertently failed to revise the note to reflect the 
fact that inspecting in accordance with paragraph (l) of this AD 
terminates the requirements of paragraph (i) of this AD. We have 
revised Note 2 of this AD to remove the statement that there is no 
terminating action for the inspections in paragraph (i) of this AD.

Request To Revise Paragraph (j)

    The commenter requests that we clarify paragraph (j) of the 
proposed AD to specify that only the holes not previously inspected in 
accordance with Boeing Alert Service Bulletin 747-53A2459, dated 
January 11, 2001, need to be inspected in accordance with that 
paragraph. The commenter points out that paragraph (g) of the proposed 
AD requires modifying the upper deck floor beams at STA 340 and STA 
360. If this modification is not done at the time of the inspection 
required by paragraph (f) of the proposed AD, paragraph (g) specifies 
that the inspection in paragraph (f) must be repeated immediately prior 
to accomplishing the modification in paragraph (g). The commenter notes 
that, after the effective date of the AD, this repeat inspection must 
be accomplished in accordance with Boeing Service Bulletin 747-53A2459, 
Revision 1, dated March 11, 2004. Thus, paragraph (j) need only require 
the inspection of holes not previously inspected by the original issue 
of the service bulletin.
    We agree with the commenter's intent, but we find that no change to 
this AD is necessary to meet the commenter's intent. Paragraph (j) of 
the proposed AD already specifies doing ``* * * inspections for 
cracking of the fastener holes inboard of the body frame that were not 
previously inspected on the STA 340 and STA 360 upper deck floor 
beams.'' After further review, however, we have determined that the 
detailed inspection that would have been required by paragraph (j) of 
this AD is the same as the one required by paragraph (f) of this AD. 
Therefore, we have revised paragraph (j) of this AD to remove the 
requirement to perform a detailed inspection.
    The commenter also requests that we allow the inspections required 
by paragraph (j) of the proposed AD to be accomplished in accordance 
with Part 6 of the Accomplishment Instructions of Boeing Service 
Bulletin 747-53A2459, Revision 1. The commenter states no rationale for 
its request.
    We do not concur. We note that the inspections and corrective 
actions specified in Part 6 of the Accomplishment Instructions of 
Boeing Service Bulletin 747-53A2459, Revision 1, are applicable only to 
airplanes modified in accordance with the initial release of Boeing 
Alert Service Bulletin 747-53A2459. No change to the AD is necessary in 
this regard.

Request To Revise Paragraph (l)

    The commenter requests that we revise paragraph (l) of the proposed 
AD to acknowledge an equivalent inspection for the purposes of 
establishing the applicable compliance time for the initial inspection 
specified in Table 3 of the proposed AD. The commenter states that an 
inspection in accordance with Part 6, Figure 14, of Boeing Service 
Bulletin 747-53A2459, Revision 1, is equivalent to an inspection in 
accordance with Figure 12 of Boeing Service Bulletin 747-53A2459, 
Revision 1. The commenter states that the same holes are covered by 
Figure 14 and Figure 12, and the same method is used for the 
inspection.
    We concur, for the reasons stated by the commenter. We have revised 
paragraph (l) of this AD to specify that, for the purposes of paragraph 
(l) and Table 3 of this AD, an inspection in accordance with Part 6, 
Figure 14, of the Accomplishment Instructions of Boeing Service 
Bulletin 747-53A2459, Revision 1, is equivalent to an inspection in 
accordance with Part 5, Figure 12, of that service bulletin.

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

    This AD will affect about 433 airplanes worldwide. The following 
table provides the estimated costs for U.S. operators to comply with 
this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Number  of
                                                                Average      Cost per      U.S.-
                     Action                      Work  hours   labor rate    airplane    registered  Fleet  cost
                                                                per hour                 airplanes
----------------------------------------------------------------------------------------------------------------
Initial inspections (required by AD 2002-18-04)            8          $65         $520          125      $65,000
Modification/permanent repair (required by AD             24           65        1,560          125      195,000
 2002-18-04)...................................
Post-mod/repair inspection (required by AD 2002-        1 24           65       11,560          125     1195,000
 18-04)........................................
One-time inspection of fastener holes inboard             24           65        1,560          N/A      2 1,560
 of the body frame (new requirement)...........
----------------------------------------------------------------------------------------------------------------
\1\ Per inspection cycle.
\2\ Per airplane.


[[Page 13351]]

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 39-12878 (67 FR 
57510, September 11, 2002), and by adding the following new 
airworthiness directive (AD):

2005-06-12 Boeing: Amendment 39-14020. Docket No. FAA-2004-19535; 
Directorate Identifier 2004-NM-78-AD.

Effective Date

    (a) This AD becomes effective April 25, 2005.

Affected ADs

    (b) This AD supersedes AD 2002-18-04, amendment 39-12878.

Applicability

    (c) This AD applies to Model 747-100, 747-100B, 747-100B SUD, 
747-200B, 747-300, 747SP, and 747SR series airplanes; line numbers 1 
through 810 inclusive; certificated in any category; and not 
equipped with a nose cargo door.

Unsafe Condition

    (d) This AD was prompted by reports of fatigue cracking of the 
upper chord of certain upper deck floor beams. We are issuing this 
AD to find and fix cracking in certain upper deck floor beams, which 
could extend and sever floor beams adjacent to the body frame and 
result in rapid depressurization and loss of controllability of 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 2002-18-04

Inspections

    (f) At the compliance time specified in paragraph (f)(1) or 
(f)(2) of this AD, as applicable, perform one-time detailed and 
open-hole high-frequency eddy current (HFEC) inspections for 
cracking in the upper deck floor beams at station (STA) 340 and STA 
360, in accordance with Boeing Alert Service Bulletin 747-53A2459, 
dated January 11, 2001; or Boeing Service Bulletin 747-53A2459, 
Revision 1, dated March 11, 2004. As of the effective date of this 
AD, only Revision 1 may be used. For the purposes of this AD, flight 
cycles with a cabin differential pressure of 2.0 psi or less are not 
calculated into the compliance thresholds specified in this AD. 
However, all cabin pressure records must be maintained for each 
airplane, and no fleet averaging of cabin pressure is allowed.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``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.''

    (1) For airplanes with 22,000 or fewer total flight cycles as of 
October 16, 2002 (the effective date of AD 2002-18-04): Do the 
inspections prior to the accumulation of 16,000 total flight cycles, 
or within 1,500 flight cycles after October 16, 2002, whichever is 
later.
    (2) For airplanes with more than 22,000 total flight cycles as 
of the effective date of this AD: Do the inspections within 500 
flight cycles after October 16, 2002.

Modification

    (g) If no crack is found during the inspections in accordance 
with paragraph (f) of this AD: Within 5,000 flight cycles after the 
initial inspections, modify the upper deck floor beams at STA 340 
and STA 360, in accordance with Boeing Alert Service Bulletin 747-
53A2459, dated January 11, 2001; or Boeing Service Bulletin 747-
53A2459, Revision 1, dated March 11, 2004. As of the effective date 
of this AD, only Revision 1 may be used. If this modification is not 
done before further flight after the inspections required by 
paragraph (f) of this AD, those inspections must be repeated one 
time, immediately before accomplishing the modification in this 
paragraph. If any crack is found during these repeat inspections, 
before further flight, accomplish paragraph (h)(2) of this AD.

Repair

    (h) If any crack is found during the inspections in accordance 
with paragraph (f) of this AD: Before further flight, repair in 
accordance with either paragraph (h)(1) or (h)(2) of this AD.
    (1) Accomplish repairs in accordance with paragraphs (h)(1)(i) 
and (h)(1)(ii) of this AD.
    (i) Accomplish a time-limited repair (including removing certain 
fasteners and the existing strap, performing open-hole HFEC 
inspections of the chord and web, stop-drilling web cracks, 
replacing the outboard section of the web, if applicable, and 
installing new straps) in accordance with Boeing Alert Service 
Bulletin 747-53A2459, dated January 11, 2001; or Boeing Service 
Bulletin 747-53A2459, Revision 1, dated March 11, 2004; except where 
the service bulletin specifies to contact Boeing for appropriate 
action, repair in accordance with a method approved by the Manager, 
Seattle Aircraft Certification Office (ACO), FAA; or in accordance 
with data meeting the type certification basis of the airplane 
approved by a Boeing Company Designated Engineering Representative 
(DER), or an Authorized Representative (AR) for the Boeing 
Delegation Option Authorization (DOA) Organization, who has been 
authorized by the Manager, Seattle ACO, to make those findings. For 
a repair method to be approved as required by this paragraph, the 
approval must specifically reference this AD. As of the effective 
date of this AD, only Revision 1 of the service bulletin may be 
used.
    (ii) Within 18 months or 1,500 flight cycles after installation 
of the time-limited repair in accordance with paragraph (h)(1)(i) of 
this AD, whichever is first, do paragraph (h)(2) of this AD.

[[Page 13352]]

    (2) Accomplish a permanent repair in accordance with Boeing 
Alert Service Bulletin 747-53A2459, dated January 11, 2001; or 
Boeing Service Bulletin 747-53A2459, Revision 1, dated March 11, 
2004; except where the service bulletin specifies to contact Boeing 
for appropriate action, 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, or an AR for the Boeing DOA Organization, who has been 
authorized by the Manager, Seattle ACO, to make such findings. For a 
repair method to be approved as required by this paragraph, the 
approval must specifically reference this AD. As of the effective 
date of this AD, only Revision 1 of the service bulletin may be 
used.

Repetitive Inspections: Post-Modification/Repair

    (i) Within 15,000 flight cycles after modification of the upper 
deck floor beams in accordance with paragraph (g) of this AD, or 
after permanent repair of the upper deck floor beams in accordance 
with paragraph (h) of this AD, as applicable: Perform either open-
hole HFEC inspections for cracking of fastener holes common to the 
upper chord, reinforcement straps, and the body frame; or surface 
HFEC inspections for cracking along the lower edge of the upper 
chord of the floor beam at the intersection with the body frame; and 
repeat these inspections at the interval specified in paragraph 
(i)(1) or (i)(2) of this AD, as applicable, until the initial 
inspection required by paragraph (l) of this AD is complete. Perform 
these inspections and repair any cracking found during these 
inspections 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, or an AR for the Boeing DOA Organization, who has been 
authorized by the Manager, Seattle ACO, to make such findings. For 
an inspection or repair method to be approved as required by this 
paragraph, the approval must specifically reference this AD.
    (1) If the most recent inspection used the surface HFEC method: 
Repeat the inspection within 1,000 flight cycles.
    (2) If the most recent inspection used the open-hole HFEC 
method: Repeat the inspection every 3,000 flight cycles.

    Note 2: Instructions for post-modification/repair inspections 
are not provided in the original issue of Boeing Alert Service 
Bulletin 747-53A2459, dated January 11, 2001.

New Requirements of This AD

One-Time Inspection for Airplanes Inspected Previously

    (j) For airplanes on which the inspection in paragraph (f) of 
this AD has been done prior to the effective date of this AD in 
accordance with Boeing Alert Service Bulletin 747-53A2459, dated 
January 11, 2001, but the modification specified in paragraph (g) or 
the permanent repair specified in paragraph (h) of this AD has not 
been done: At the applicable time specified in Table 1 of this AD, 
do a one-time open-hole HFEC inspection for cracking of the fastener 
holes inboard of the body frame that were not previously inspected 
on the STA 340 and STA 360 upper deck floor beams. Do this 
inspection in accordance with Part 1 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2459, Revision 1, 
dated March 11, 2004.

              Table 1.--Compliance Times for Paragraph (j)
------------------------------------------------------------------------
   Total number of accumulated flight
cycles as of the effective date of this          Compliance time
                   AD
------------------------------------------------------------------------
22,000 or fewer........................  Within 5,000 flight cycles
                                          after the initial open-hole
                                          HFEC inspection for cracking
                                          in accordance with paragraph
                                          (f) of this AD, or within
                                          1,000 flight cycles after the
                                          effective date of this AD,
                                          whichever is later.
22,001 or more.........................  Prior to the accumulation of
                                          25,000 total flight cycles, or
                                          within 1,000 flight cycles
                                          after the effective date of
                                          this AD, whichever is later.
------------------------------------------------------------------------

One-Time Inspection for Airplanes Modified/Repaired Previously

    (k) For airplanes on which the modification specified in 
paragraph (g) or the permanent repair specified in paragraph (h) of 
this AD has been done prior to the effective date of this AD in 
accordance with Boeing Alert Service Bulletin 747-53A2459, dated 
January 11, 2001: At the applicable time specified in Table 2 of 
this AD, do a one-time open-hole HFEC inspection for cracking of 
fastener holes common to the modification straps, in accordance with 
Part 6 of the Accomplishment Instructions of Boeing Service Bulletin 
747-53A2459, Revision 1, dated March 11, 2004.

              Table 2.--Compliance Times for Paragraph (k)
------------------------------------------------------------------------
   Total number of accumulated flight
    cycles when the modification or              Compliance time
       permanent repair was done
------------------------------------------------------------------------
22,000 or fewer........................  Within 3,000 flight cycles
                                          after doing the modification
                                          or permanent repair, or 1,000
                                          flight cycles after the
                                          effective date of this AD,
                                          whichever is later.
22,001 or more.........................  Within 1,500 flight cycles
                                          after doing the modification
                                          or permanent repair, or 1,000
                                          flight cycles after the
                                          effective date of this AD,
                                          whichever is later.
------------------------------------------------------------------------

Repetitive Inspections: Post-Modification/Repair

    (l) Do open-hole HFEC inspections for cracking of the STA 340 
and STA 360 upper deck floor beams at fastener holes common to the 
upper chord, reinforcement straps, and body frame; or do surface 
HFEC inspections for cracking along the lower edge of the upper 
chord and reinforcement straps of the floor beams. Do the applicable 
inspection in accordance with Part 5 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2459, Revision 1, 
dated March 11, 2004. Do the initial inspections at the applicable 
times specified in Table 3 of this AD, and repeat the inspection at 
the applicable interval specified in Figure 9 of the service 
bulletin. Completing the initial inspection required by this 
paragraph terminates the repetitive inspections required by 
paragraph (i) of this AD. For airplanes on which paragraph (i) of 
this AD has not been done, doing the initial inspection required by 
this paragraph at the specified compliance time eliminates the need 
to comply with paragraph (i) of this AD. For the purposes of this 
paragraph and Table 3 of this AD, an inspection in accordance with 
Part 6, Figure 14, of the Accomplishment Instructions of Boeing 
Service Bulletin 747-53A2459, Revision 1, is equivalent to an 
inspection in accordance with Part 5, Figure 12, of the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2459, 
Revision 1.

 

[[Page 13353]]

      Table 3.--Compliance Times for Initial Inspection Required By
                              Paragraph(l)
------------------------------------------------------------------------
 For the inspections identified
    in the following figures           For these      Do the inspection--
  referenced in Figure 9 of the       airplanes--
       service bulletin--
------------------------------------------------------------------------
Figure 10 or 11.................  Airplanes not       Within 15,000
                                   inspected           flight cycles
                                   previously in       after doing the
                                   accordance with     modification or
                                   paragraph (i) of    permanent repair.
                                   this AD.
Figure 10 or 11.................  Airplanes           Within 1,000
                                   inspected           flight cycles
                                   previously in       after the most
                                   accordance with     recent
                                   paragraph (i) of    inspection.
                                   this AD using the
                                   surface HFEC
                                   method for the
                                   most recent
                                   inspection.
Figure 10 or 11.................  Airplanes           Within 3,000
                                   inspected           flight cycles
                                   previously in       after the most
                                   accordance with     recent
                                   paragraph (i) of    inspection.
                                   this AD using the
                                   open-hole HFEC
                                   method for the
                                   most recent
                                   inspection.
Figure 12 or 13.................  All airplanes.....  Within 6,000
                                                       flight cycles
                                                       after doing the
                                                       modification or
                                                       permanent repair,
                                                       or within 1,000
                                                       flight cycles
                                                       after the
                                                       effective date of
                                                       this AD,
                                                       whichever is
                                                       later.
------------------------------------------------------------------------

Repair

    (m) If any crack is found during any inspection required by 
paragraph (j), (k), or (l) of this AD: Before further flight, repair 
in accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 747-53A2459, Revision 1, dated March 11, 2004; except where 
the service bulletin specifies to contact Boeing for appropriate 
action, 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 an AR for the Boeing 
DOA Organization who has been authorized by the Manager, Seattle 
ACO, to make such findings. For a repair method to be approved, the 
approval must specifically reference this AD.

Reporting Not Required

    (n) Although Boeing Service Bulletin 747-53A2459, Revision 1, 
dated March 11, 2004, specifies to report certain body frame cracks 
on certain airplanes, this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, Seattle ACO, has the authority to approve 
AMOCs for this AD, if requested using 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 AR 
for the Boeing DOA Organization who has been authorized by the 
Manager, Seattle ACO, to make such findings.
    (3) AMOCs approved previously in accordance with AD 2002-18-04 
are approved as alternative methods of compliance with paragraphs 
(f), (g), (h), and (i) of this AD.

Material Incorporated by Reference

    (p) You must use Boeing Alert Service Bulletin 747-53A2459, 
dated January 11, 2001; or Boeing Service Bulletin 747-53A2459, 
Revision 1, dated March 11, 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 Service Bulletin 747-53A2459, 
Revision 1, dated March 11, 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-
53A2459, dated January 11, 2001, as of October 16, 2002 (67 FR 
57510, September 11, 2002).
    (3) The Director of the Federal Register approves the 
incorporation by reference of these documents in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. For copies of the service 
information, contact Boeing Commercial Airplanes, P.O. Box 3707, 
Seattle, Washington 98124-2207. For information on the availability 
of this material at the National Archives and Records Administration 
(NARA), call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. You may view the AD docket at the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street SW, 
room PL-401, Nassif Building, Washington, DC.

    Issued in Renton, Washington, on March 9, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-5388 Filed 3-18-05; 8:45 am]
BILLING CODE 4910-13-P