[Federal Register Volume 64, Number 4 (Thursday, January 7, 1999)]
[Rules and Regulations]
[Pages 985-986]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-186]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 64, No. 4 / Thursday, January 7, 1999 / Rules
and Regulations
[[Page 985]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-308-AD; Amendment 39-10982; AD 97-20-01 R1]
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 revises an existing airworthiness directive
(AD), applicable to certain Boeing Model 747 series airplanes, that
currently requires repetitive inspections to detect cracks, corrosion,
or damage of the lower spar fitting body and lug, and corrective
actions, if necessary. That AD also provides for optional terminating
action for the repetitive inspection requirements. That AD was prompted
by reports that fatigue cracking was found in the lower spar fitting
lug on the number 3 pylon and in the lower spar fitting body. The
actions specified by that AD are intended to detect and correct such
fatigue cracking, which could result in failure of the strut and
separation of the engine from the airplane. This amendment references
additional service bulletins for accomplishment of the optional
replacement, and clarifies that accomplishment of certain AD's
terminates the repetitive inspections.
DATES: Effective February 11, 1999.
The incorporation by reference of certain publications, as listed
in the regulations, was approved previously by the Director of the
Federal Register as of October 7, 1997 (62 FR 49431, September 22,
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 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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by revising AD 97-20-01,
amendment 39-10139 (62 FR 49431, September 22, 1997), which is
applicable to certain Boeing Model 747 series airplanes, was published
in the Federal Register on April 3, 1998 (63 FR 16449). That action
proposed to continue to require repetitive inspections to detect
cracks, corrosion, or damage of the lower spar fitting body and lug,
and corrective actions, if necessary. The action also proposed to
provide for optional terminating action for the repetitive inspection
requirements.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for the Proposal
Two commenters support the proposed rule.
Requests To Withdraw the Proposal
Two commenters state that the proposed revision of AD 97-20-01 is
not necessary because the intent of the revision was approved
previously by the FAA under the ``global'' alternative method of
compliance (AMOC) 97-120S-743, which was issued to Boeing on November
12, 1997, and under Boeing letter B-T113-97-5439, dated November 5,
1997.
The FAA infers from these remarks that the commenters request that
the proposed AD be withdrawn. The FAA does not concur. Although the FAA
agrees that the intent of the proposed revision to AD 97-20-01 is the
same as the previously referenced AMOC for that AD, the FAA has
determined that the revision to that AD is necessary. First, the
revision clarifies the requirements for any future operators who may
not be aware of an existing AMOC. Second, any non-U.S. registered
airplanes that are subsequently placed on the U.S. Register will be
required to comply with the revision to AD 97-20-01. In addition, the
revision will assist FAA principal maintenance inspectors in
determining compliance with the final rule. In light of these factors,
the FAA considers it necessary to issue the final rule. Paragraph
(c)(2) has been added to the final rule to clarify that AMOC's,
approved previously in accordance with AD 97-20-01, are approved as
AMOC's with the requirements of this AD.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed. The FAA has
determined that these changes will neither increase the economic burden
on any operator nor increase the scope of the AD.
Cost Impact
There are approximately 367 Model 747 series airplanes of the
affected design in the worldwide fleet. The FAA estimates that 152
airplanes of U.S. registry will be affected by this AD, that it will
take approximately 19 work hours per airplane to accomplish the
required inspections, and that the average labor rate is $60 per work
hour. Based on these figures, the cost impact of the inspections
required by this AD on U.S. operators is estimated to be $173,280, or
$1,140 per airplane, per inspection cycle.
The cost impact figure discussed above is 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 substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
[[Page 986]]
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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
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 39-10139 (62 FR
49431, September 22, 1997) and by adding a new airworthiness directive
(AD), amendment 39-10982, to read as follows:
97-20-01 R1 Boeing: Amendment 39-10982. Docket 97-NM-308-AD.
Revises AD 97-20-01, Amendment 39-10139.
Applicability: Model 747 series airplanes, having line numbers 1
through 500 inclusive, equipped with Pratt & Whitney Model JT9D-3, -
7, or -7Q engines, or having line numbers 202, 204, 232, or 257,
equipped with General Electric Model CF6 series engines;
certificated in any category; and on which the strut/wing
modification has not been accomplished in accordance with either of
the following AD's:
AD 95-10-16, amendment 39-9233 (60 FR 27008, May 22,
1995), or
AD 95-13-07, amendment 39-9287 (60 FR 33336, June 28,
1995).
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 (c)(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 in the lower spar fitting
lug or the lower spar fitting body, which could result in failure of
the strut and separation of the engine from the airplane, accomplish
the following:
(a) Within 90 days after October 7, 1997 (the effective date of
AD 97-20-01, amendment 39-10139) perform a detailed visual
inspection and an ultrasonic inspection to detect cracks, corrosion,
or damage of the lower spar fitting body and lug, as applicable, in
accordance with Figures 9 and 10 of Boeing Service Bulletin 747-54-
2062, Revision 8, dated August 21, 1997.
Note 2: This AD does not require an inspection of the inboard
strut-to-diagonal brace attach fitting as described in Figure 1 of
Boeing Service Bulletin 747-54-2062, Revision 8, dated August 21,
1997. However, this inspection is required to be accomplished as
part of AD 95-20-05, amendment 39-9383 (60 FR 51705, October 10,
1995).
(1) If no crack, corrosion, or damage is detected, repeat the
detailed visual and ultrasonic inspections thereafter at intervals
not to exceed 400 landings.
(2) If any crack, corrosion, or damage is detected, prior to
further flight, accomplish either paragraph (a)(2)(i) or (a)(2)(ii)
of this AD.
(i) Replace the lower spar fitting with a new steel lower spar
fitting, in accordance with Part II of the Accomplishment
Instructions of the service bulletin. Or
(ii) Modify the nacelle strut and wing structure in accordance
with AD 95-10-16, amendment 39-9233 (60 FR 27008, May 22, 1995), or
AD 95-13-07, amendment 39-9287 (60 FR 33336, June 28, 1995).
(b) Replacement of the lower spar fitting with a new steel lower
spar fitting, in accordance with Part II of the Accomplishment
Instructions of any of the following service bulletins listed below,
or accomplishment of modification of the nacelle strut and wing
structure required by AD 95-10-16, amendment 39-9233 (60 FR 27008,
May 22, 1995), or AD 95-13-07, amendment 39-9287 (60 FR 33336, June
28, 1995); constitutes terminating action for the repetitive
inspection requirements of this AD.
Boeing Service Bulletin 747-54-2062, Revision 1, dated
November 13, 1980;
Boeing Service Bulletin 747-54-2062, Revision 2, dated
March 19, 1981;
Boeing Service Bulletin 747-54-2062, Revision 3, dated
August 28, 1981;
Boeing Service Bulletin 747-54-2062, Revision 4, dated
June 30, 1982;
Boeing Service Bulletin 747-54-2062, Revision 5, dated
June 1, 1984;
Boeing Service Bulletin 747-54-2062, Revision 6, dated
October 2, 1986;
Boeing Service Bulletin 747-54-2062, Revision 7, dated
December 21, 1994;
Boeing Service Bulletin 747-54-2062, Revision 8, dated
August 21, 1997.
(c)(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 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.
(2) Alternative methods of compliance, approved previously in
accordance with AD 97-20-01, are approved as alternative methods of
compliance with the requirements 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.
(d) 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.
(e) Certain actions shall be done in accordance with Boeing
Service Bulletin 747-54-2062, Revision 8, dated August 21, 1997. The
incorporation by reference of this document was approved previously
by the Director of the Federal Register, in accordance with 5 U.S.C.
552(a) and 1 CFR part 51, as of October 7, 1997 (62 FR 49431,
September 22, 1997). 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,
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
(f) This amendment becomes effective on February 11, 1999.
Issued in Renton, Washington, on December 30, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-186 Filed 1-6-99; 8:45 am]
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