[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]
BILLING CODE 4910-13-U