[Federal Register Volume 68, Number 159 (Monday, August 18, 2003)]
[Rules and Regulations]
[Pages 49342-49344]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-20714]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-228-AD; Amendment 39-13265; AD 2003-16-12]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Boeing Model 747 series airplanes, that 
currently requires inspections to detect cracking of the front spar web 
of the wing, and corrective action if necessary. This amendment adds 
one airplane to the applicability, changes certain compliance times, 
adds certain new requirements, and provides an optional modification. 
This action is necessary to detect and correct fatigue cracking of the 
front spar web, which could result in fuel leaking onto an engine and a 
consequent fire. This action is intended to address the identified 
unsafe condition.

DATES: Effective September 22, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 22, 2003.
    The incorporation by reference of Boeing Alert Service Bulletin 
747-57A2311, dated January 27, 2000, as listed in the regulations, was 
approved previously by the Director of the Federal Register as of 
January 30, 2001 (65 FR 81331, December 26, 2000).

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, PO 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 Anderson, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6421; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-25-12, 
amendment 39-12047 (65 FR 81331, December 26, 2000), which is 
applicable to certain Boeing Model 747 series airplanes, was published 
in the Federal Register on March 4, 2003 (68 FR 10185). The action 
proposed to continue to require inspections to detect cracking of the 
front spar web of the wing, and corrective action if necessary. That 
action also proposed to add one airplane to the applicability, change 
certain compliance times, add certain new requirements, and proposed an 
optional modification.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Change to Final Rule

    After reviewing paragraph (g) of the proposed AD, the FAA finds it 
necessary to clarify the applicability specified for the post-
modification inspections. Paragraph (g) states, ``For airplanes on 
which the actions specified in paragraph (b) or (f) of this AD have 
been done before the effective date of this AD: In lieu of the 
inspections * * *'' We inadvertently included ``before the effective 
date of this AD;'' however, paragraph (g) is an option for airplanes on 
which paragraph (b) or (f) has been done either before or after the 
effective date of the AD. Therefore, we have changed paragraph (g) of 
this final rule for clarification.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule with the change previously described. 
This change will neither increase the economic burden on any operator 
nor increase the scope of the AD.

Changes to 14 CFR Part 39/Effect on the AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance. However, for clarity and consistency in this final rule, we 
have retained the language of the NPRM regarding that material.

Change to Labor Rate Estimate

    We have reviewed the figures we have used over the past several 
years to calculate AD costs to operators. To account for various 
inflationary costs in the airline industry, we find it necessary to 
increase the labor rate used in these calculations from $60 per work 
hour to $65 per work hour. The cost impact information, below, reflects 
this increase in the specified hourly labor rate.

Cost Impact

    There are approximately 479 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 97 airplanes of U.S. registry 
will be affected by this AD.
    The external inspections that are currently required by AD 2000-25-
12 take approximately 48 work hours per airplane to accomplish, at an 
average labor rate of $65 per work hour. Based on these figures, the 
cost impact of the AD on U.S. operators is estimated to be $3,120 per 
airplane, per inspection cycle.
    The new inspections that are required by this new AD will take 
approximately 74 work hours per airplane to accomplish, at an average 
labor rate of $65 per work hour. Based on these figures, the cost 
impact of the new

[[Page 49343]]

inspections is estimated to be $4,810 per airplane, per inspection 
cycle.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.
    Should an operator elect to accomplish the optional modification 
that is provided by this AD, it will take approximately 40 work hours 
to accomplish, at an average labor rate of $65 per work hour. The cost 
of required parts will be between $8,606 and $28,036 per airplane. 
Based on these figures, the cost impact of the optional modification 
will be between $11,206 and $30,636 per airplane.

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 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

0
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

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. Section 39.13 is amended by removing amendment 39-12047 (65 FR 8128, 
December 26, 2000) and by adding the following new airworthiness 
directive:

2003-16-12 Boeing: Amendment 39-13265. Docket 2001-NM-228-AD. 
Supersedes AD 2000-25-12, amendment 39-12047.

    Applicability: Model 747 series airplanes, as listed in Boeing 
Service Bulletin 747-57A2311, Revision 2, dated February 21, 2002; 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (h)(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 detect and correct fatigue cracking of the front spar web of 
the wing, which could result in fuel leaking onto an engine and a 
consequent fire, accomplish the following:

Restatement of Certain Requirements of AD 2000-25-12

Repetitive Inspections

    (a) Excluding Group 31 airplanes, as specified in Boeing Service 
Bulletin 747-57A2311, Revision 2, dated February 21, 2002: At the 
later of the times specified in paragraphs (a)(1) and (a)(2) of this 
AD, except as provided by paragraph (b) of this AD, perform the Part 
1 external web inspection--including detailed, ultrasonic, and high 
frequency eddy current (HFEC) inspections--to detect cracking of the 
front spar web of the wing, in accordance with Boeing Alert Service 
Bulletin 747-57A2311, dated January 27, 2000. Repeat the inspections 
thereafter at intervals not to exceed 2,000 flight cycles until 
accomplishment of the inspections required by paragraph (e) of this 
AD. Accomplishment of an optional inspection of the front spar web 
per AD 2000-25-12, amendment 39-12047, is considered acceptable for 
compliance with the applicable inspection requirement in this 
paragraph.

    Note 2: For the purposes of this AD, a detailed 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.''

    (1) Prior to the accumulation of 13,000 total flight cycles or 
30,000 total flight hours, whichever occurs first.
    (2) Within 18 months after January 30, 2001 (the effective date 
of AD 2000-25-12, amendment 39-12047).

Exception for Modified Airplanes

    (b) Except as provided by paragraph (g) of this AD, for 
airplanes on which the front spar web between front spar station 
inboard (FSSI) 668 and FSSI 692 has been replaced before the 
effective date of this AD with a shot-peened front spar web, in 
accordance with AD 99-10-09, amendment 39-11162: Within 13,000 
flight cycles or 30,000 flight hours after the replacement, 
whichever occurs first, inspect the new section of the front spar 
web that overlaps with the inspection area specified in Boeing Alert 
Service Bulletin 747-57A2311 (the area between FSSI 668 and FSSI 
684), dated January 27, 2000. Repeat the inspections thereafter, in 
accordance with paragraph (a) of this AD.

Repair

    (c) If any cracking is detected during any inspection required 
by this AD, prior to further flight, 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 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 approval letter must specifically reference this AD.

New Requirements of This AD

Compliance Times

    (d) Where the compliance time inspection threshold is measured 
from the release of either Boeing Alert Service Bulletin 747-
57A2311, Revision 1, including Appendices A and B, dated June 14, 
2001; or Boeing Service Bulletin 747-57A2311, Revision 2, dated 
February 21, 2002: This AD requires compliance within the inspection 
interval specified in the service bulletin ``after the effective 
date of this AD.''

Repetitive Inspections

    (e) Except as provided by paragraph (g) of this AD: Do detailed, 
ultrasonic, and HFEC inspections, as applicable, to find cracking of 
the front spar web of the wing, in accordance with Part 1 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2311, Revision 1, including Appendices A and B, dated June 14, 
2001; or

[[Page 49344]]

Boeing Service Bulletin 747-57A2311, Revision 2, dated February 21, 
2002. Do the inspections at the applicable initial inspection 
threshold times specified in Figure 1, Tables 1 through 8 inclusive, 
of the service bulletin. Repeat the applicable inspection thereafter 
at the applicable repeat inspection interval specified in Figure 1, 
Tables 1 through 8 inclusive, of the service bulletin. 
Accomplishment of the inspections required by this paragraph 
terminates the repetitive inspections required by paragraph (a) of 
this AD.

Optional Modification

    (f) Accomplishment of the optional modification of the front 
spar web of the wing (includes removing the existing fasteners and 
doing an open hole, rotating probe HFEC inspection of the holes for 
web cracks; and if no cracks are found, oversizing the holes, and 
installing tension type fasteners), in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2311, Revision 1, including Appendices A and B, dated June 14, 
2001; or Boeing Service Bulletin, Revision 2, dated February 21, 
2002; terminates the repetitive inspections required by paragraph 
(e) of this AD.

Post-Modification Inspections

    (g) For airplanes on which the actions specified in paragraph 
(b) or (f) of this AD have been done: In lieu of the inspections 
required by paragraph (b) or (e) of this AD, as applicable, do the 
applicable post-modification inspection specified in Part 1 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2311, Revision 1, including Appendices A and B, dated June 14, 
2001; or Boeing Service Bulletin 747-57A2311, Revision 2, dated 
February 21, 2002; at the post-modification inspection threshold 
times specified in Figure 1, Tables 1 through 8 inclusive, of the 
service bulletin. Repeat the applicable inspection thereafter at the 
applicable post-modification repeat inspection interval specified in 
Figure 1, Tables 1 through 8 inclusive, of the service bulletin.

Alternative Methods of Compliance

    (h)(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 2000-25-12, amendment 39-12047, are approved as 
alternative methods of compliance with paragraph (c) of this AD.

    Note 3: 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

    (i) Special flight permits may be issued in accordance with 
sections 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

    (j) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Boeing Alert Service Bulletin 747-57A2311, 
dated January 27, 2000; and Boeing Alert Service Bulletin 747-
57A2311, Revision 1, including Appendices A and B, dated June 14, 
2001; or Boeing Service Bulletin 747-57A2311, Revision 2, dated 
February 21, 2002; as applicable.
    (1) The incorporation by reference of Boeing Alert Service 
Bulletin 747-57A2311, Revision 1, including Appendices A and B, 
dated June 14, 2001; and Boeing Service Bulletin 747-57A2311, 
Revision 2, dated February 21, 2002; 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 747-57A2311, dated January 27, 2000, was approved 
previously by the Director of the Federal Register as of January 30, 
2001 (65 FR 81331, December 26, 2000).
    (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.

Effective Date

    (k) This amendment becomes effective on September 22, 2003.

    Issued in Renton, Washington, on August 7, 2003.
Neil D. Schalekamp,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-20714 Filed 8-15-03; 8:45 am]
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