[Federal Register Volume 63, Number 239 (Monday, December 14, 1998)]
[Rules and Regulations]
[Pages 68672-68674]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-32811]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-227-AD; Amendment 39-10941; AD 98-25-15]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain McDonnell Douglas Model MD-11 series airplanes.
This amendment requires inspections to detect attachment failures of
the 12 attachments located on the No. 4 banjo fitting/pylon carry-
through cap, and to detect cracking of the forward and aft flanges and
bolt holes of the No. 4 banjo fitting; repair, if necessary; and
replacement of the 12 attachments with new or serviceable parts. Such
replacement terminates the repetitive inspections. This amendment is
prompted by a report indicating that attachment bolts on the forward
and aft flanges of the No. 4 banjo fitting and the pylon carry-through
cap failed due to fatigue cracking. The actions specified by this AD
are intended to prevent such cracking, which could result in reduced
controllability of the airplane during flight and ground operations.
DATES: Effective January 19, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 19, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from The Boeing Company, Douglas Products Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Technical
Publications Business Administration, Dept. C1-L51 (2-60). 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 FAA, Transport Airplane Directorate,
Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: John L. Cecil, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California 90712; telephone (562) 627-5229; fax (562) 627-
5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain McDonnell Douglas Model
MD-11 series airplanes was published in the Federal Register on
September 17, 1998 (63 FR 49679). That action proposed to require
inspections to detect attachment failures of the 12 attachments located
on the No. 4 banjo fitting/pylon carry-through cap, and to detect
cracking of the forward and aft flanges and bolt holes of the No. 4
banjo fitting; repair, if necessary; and replacement of the 12
attachments with new or serviceable parts. Such replacement would
terminate the repetitive inspections.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Both commenters support the proposed rule.
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.
Cost Impact
There are approximately 82 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 31 airplanes of U.S. registry
will be affected by this AD.
The FAA estimates that it will take approximately 1 work hour per
airplane to accomplish the required external visual inspection, at an
average labor rate of $60 per work hour. Based on
[[Page 68673]]
these figures, the cost impact of the external visual inspection
required by this AD on U.S. operators is estimated to be $1,860, or $60
per airplane, per inspection cycle.
The FAA estimates that it will take approximately 2 work hours per
airplane to accomplish the required eddy current inspection, at an
average labor rate of $60 per work hour. Based on these figures, the
cost impact of the eddy current inspection required by this AD on U.S.
operators is estimated to be $3,720, or $120 per airplane.
The FAA estimates that it will take approximately 6 work hours per
airplane to accomplish the required replacement, at an average labor
rate of $60 per work hour. Required parts will cost approximately $250
per airplane. Based on these figures, the cost impact of the
replacement required by this AD on U.S. operators is estimated to be
$18,910, or $610 per airplane.
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 substantial direct
effects 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, 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 adding the following new
airworthiness directive:
98-25-15 McDonnell Douglas: Amendment 39-10941. Docket 96-NM-227-AD.
Applicability: Model MD-11 series airplanes; as listed in
McDonnell Douglas Service Bulletin MD11-55-013, Revision 03, dated
May 15, 1998; 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 (e) 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 failure of the attachment bolts on the forward and
aft flanges of the No. 4 banjo fitting and the pylon carry-through
cap due to fatigue cracking, and consequent reduced controllability
of the airplane during flight and ground operation, accomplish the
following:
(a) Within 1,500 landings after the effective date of this AD,
perform an external visual inspection for attachment failures of the
12 attachments located on the No. 4 banjo fitting/pylon carry-
through cap, in accordance with McDonnell Douglas Service Bulletin
MD11-55-013, Revision 02, dated October 28, 1996; or Revision 03,
dated May 15, 1998.
(1) If no failed attachment is found, repeat the external visual
inspection thereafter at intervals not to exceed 1,500 landings
until the terminating action specified in paragraph (b) of this AD
is accomplished.
(2) If any failed attachment is found, prior to further flight,
accomplish the actions specified in paragraph (b) of this AD.
(b) Except as provided by paragraph (c) of this AD: Within 5
years after the effective date of this AD, perform an eddy
inspection to detect cracking of the forward and aft flanges and
bolt holes of the No. 4 banjo fitting, in accordance with McDonnell
Douglas MD-11 Service Bulletin 55-13, Revision 1, dated December 17,
1993; or McDonnell Douglas Service Bulletin MD11-55-013, Revision
02, dated October 28, 1996; or McDonnell Douglas Service Bulletin
MD11-55-013, Revision 03, dated May 15, 1998.
(1) If no cracking is found, within 5 years after the effective
date of this AD, replace the 12 attachments located on the No. 4
banjo fitting/pylon carry-through cap with new or serviceable
attachments in accordance with Revision 03 of the service bulletin.
Such replacement constitutes terminating action for the repetitive
inspections required by paragraph (a)(1) of this AD.
(2) If any cracking is found, prior to further flight, repair
the fitting, and replace the 12 attachments located on the No. 4
banjo fitting/pylon carry-through cap with new or serviceable
attachments in accordance with Revision 03 of the service bulletin.
Such replacement constitutes terminating for the repetitive
inspections required by paragraph (a)(1) of this AD.
(c) For airplanes on which McDonnell Douglas MD-11 Service
Bulletin 55-13, dated December 22, 1992, has been accomplished, and
on which no failed attachment was found during the inspection
required by paragraph (a) of this AD: The eddy current bolt hole
inspection specified in paragraph (b) of this AD is not required
provided that all 12 attachments have been replaced in accordance
with the original issue of the service bulletin.
(d) If the service bulletin specifies that the manufacturer may
be contacted for disposition of enlargement of holes beyond the
specifications of the service bulletin, or for an evaluation for
deferment of repairs: Those conditions shall be addressed in
accordance with a method approved by the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate.
(e) 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, Los Angeles ACO. Operators shall
submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Los Angeles ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
(f) 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.
(g) Except as provided by paragraph (d) of this AD, the actions
shall be done in accordance with McDonnell Douglas MD-11 Service
Bulletin 55-13, Revision 1, dated December 17, 1993; McDonnell
Douglas Service Bulletin MD11-55-013, Revision 02, dated October 28,
1996; or McDonnell Douglas Service Bulletin MD11-55-013, Revision
03, dated May 15, 1998; as
[[Page 68674]]
applicable. This incorporation by reference was approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Copies may be obtained from The Boeing Company,
Douglas Products Division, 3855 Lakewood Boulevard, Long Beach,
California 90846, Attention: Technical Publications Business
Administration, Dept. C1-L51 (2-60). Copies may be inspected at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
(h) This amendment becomes effective on January 19, 1999.
Issued in Renton, Washington, on December 4, 1998.
John W. McGraw,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-32811 Filed 12-11-98; 8:45 am]
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