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[Federal Register Volume 65, Number 103 (Friday, May 26, 2000)]
[Rules and Regulations]
[Pages 34061-34063]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-13086]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-88-AD; Amendment 39-11748; AD 2000-10-23]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-100, -200, -300, 
747SR, and 747SP 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 747-100, -200, -300, 747SR, 
and 747SP series airplanes, that currently requires a one-time 
inspection to detect cracking of the longeron splice fittings at 
stringer 11, on the left and right sides at body station 2598, and 
replacement of any cracked fitting with a new fitting. This amendment 
reduces the compliance time for accomplishment of the currently 
required inspection and adds a new requirement for repetitive 
inspections. This amendment is prompted by reports that fatigue 
cracking was found on longeron splice fittings. The actions specified 
by this AD are intended to detect and correct such fatigue cracking, 
which could result in reduced controllability of the horizontal 
stabilizer.

DATES: Effective June 30, 2000.
    The incorporation by reference of Boeing Alert Service Bulletin 
747-53A2410, Revision 2, including Addendum, dated October 30, 1997, as 
listed in the regulations, is approved by the Director of the Federal 
Register as of June 30, 2000.
    The incorporation by reference of Boeing Service Bulletin 747-
53A2410, Revision 3, including Addendum, dated March 12, 1998, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of January 13, 1998 (62 FR 67550, December 29 
1997).

ADDRESSES: 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 Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 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: Rick Kawaguchi, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-1153; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 97-26-21, 
amendment 39-10264 (62 FR 67550, December 29 1997), which is applicable 
to certain Boeing Model 747-100, -200, -300, 747SR, and 747SP series 
airplanes, was published in the Federal Register on February 22, 2000 
(65 FR 8667). The action proposed to continue to require a one-time 
inspection to detect cracking of the longeron splice fittings at 
stringer 11, on the left and right sides at body station 2598, and 
replacement of any cracked fitting with a new fitting. The action also 
proposed to reduce the compliance time for accomplishment of the 
currently required inspection and add a new requirement for repetitive 
inspections.

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.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 685 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 99 airplanes of U.S. registry 
will be affected by this AD.
    The inspection that is currently required by AD 97-26-21 takes 
approximately 32 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour.
    Based on these figures, the cost impact of the currently required 
actions on U.S. operators is estimated to be $190,080, or $1,920 per 
airplane.
    This AD requires the same inspection currently required by AD 97-
26-21 to be accomplished repetitively. Therefore, the cost impact of 
the requirements of this AD on U.S. operators is estimated to be 
$190,080, or $1,920 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.

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

[[Page 34062]]

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

    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 39-10264 (62 FR 
67550, December 29 1997), and by adding a new airworthiness directive 
(AD), amendment 39-11748, to read as follows:

2000-10-23  Boeing: Amendment 39-11748. Docket 97-NM-88-AD. 
Supersedes AD 97-26-21, Amendment 39-10264.

    Applicability: Model 747-100, 747-200, 747-300, 747SR, and 747SP 
series airplanes; having line positions 201 through 886 inclusive; 
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 (d) 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 longeron splice 
fittings at stringer 11, which could result in reduced 
controllability of the horizontal stabilizer, accomplish the 
following:

Initial Inspection

    (a) Perform a one-time detailed visual inspection to detect 
cracking of the longeron fittings at stringer 11, on the left and 
right sides at body station 2598, at the time specified in paragraph 
(a)(1) or (a)(2) of this AD, as applicable, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2410, Revision 2, dated October 30, 1997, including Addendum; or 
Boeing Service Bulletin 747-53A2410, Revision 3, dated March 12, 
1998, including Addendum. After the effective date of this AD, only 
Revision 3 shall be used.
    (1) For airplanes that have accumulated fewer than 17,000 total 
flight cycles or 63,000 total flight hours as of the effective date 
of this AD: Inspect at the later of the times specified in paragraph 
(a)(1)(i) or (a)(1)(ii) of this AD.
    (i) Prior to the accumulation of 17,000 total flight cycles or 
63,000 total flight hours, whichever occurs first.
    (ii) Within 1,800 flight cycles or 7,000 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For airplanes that have accumulated 17,000 total flight 
cycles or more, or 63,000 total flight hours or more, as of the 
effective date of this AD: Inspect at the earlier of the times 
specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.
    (i) Prior to the accumulation of 22,000 total flight cycles or 
78,000 total flight hours, whichever occurs first.
    (ii) Within 1,800 flight cycles or 7,000 flight hours after the 
effective date of this AD, whichever occurs first.

    Note 2: Where there are differences between the AD and the 
service bulletin, the AD prevails.

    Note 3: 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 Inspections

    (b) If no crack is found during the inspection required by 
paragraph (a) of this AD, repeat the inspection one time at the 
later of the times specified in paragraphs (b)(1) and (b)(2) of this 
AD, and thereafter at intervals not to exceed 3,000 flight cycles or 
18,000 flight hours, whichever occurs first.
    (1) Within 3,000 flight cycles or 18,000 flight hours after 
accomplishment of the most recent inspection, whichever occurs 
first.
    (2) Within 1,800 flight cycles or 7,000 flight hours after the 
effective date of this AD, whichever occurs first.

Replacement and Repetitive Inspections

    (c) If any crack is found during any inspection required by 
paragraph (a) or (b) of this AD: Prior to further flight, replace 
the cracked fitting with a new fitting, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2410, Revision 2, dated October 30, 1997, including Addendum; or 
Boeing Service Bulletin 747-53A2410, Revision 3, dated March 12, 
1998, including Addendum. After the effective date of this AD, only 
Revision 3 shall be used. Then, repeat the inspection specified in 
paragraph (a) of this AD at the later of the times specified in 
paragraphs (c)(1) and (c)(2) of this AD, and thereafter at intervals 
not to exceed 3,000 flight cycles or 18,000 flight hours, whichever 
occurs first.
    (1) Within 17,000 flight cycles or 63,000 flight hours after 
replacement, whichever occurs first.
    (2) Within 1,800 flight cycles or 7,000 flight hours after the 
effective date of this AD, whichever occurs first.

Alternative Methods of Compliance

    (d) 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 Aircraft Certification 
Office (ACO), FAA, Transport Airplane Directorate. 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.

    Note 4: 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

    (e) 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

    (f) The actions shall be done in accordance with Boeing Alert 
Service Bulletin 747-53A2410, Revision 2, including Addendum, dated 
October 30, 1997; or Boeing Service Bulletin 747- 53A2410, Revision 
3, including Addendum, dated March 12, 1998.
    (1) The incorporation by reference of Boeing Service Bulletin 
747-53A2410, Revision 3, including Addendum, dated March 12, 1998, 
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 747-53A2410, Revision 2, including Addendum, dated October 
30, 1997, was approved previously by the Director of the Federal 
Register as of January 13, 1998 (62 FR 67550, December 29 1997).
    (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.
    (g) This amendment becomes effective on June 30, 2000.

[[Page 34063]]

    Issued in Renton, Washington, on May 18, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-13086 Filed 5-25-00; 8:45 am]
BILLING CODE 4910-13-U
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