[Federal Register Volume 62, Number 85 (Friday, May 2, 1997)]
[Rules and Regulations]
[Pages 24019-24021]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-10788]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-278-AD; Amendment 39-10003; AD 97-09-07]
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 supersedes an existing airworthiness directive 
(AD), applicable to certain McDonnell Douglas Model MD-11 series 
airplanes, that currently requires inspections to detect damage of the 
support brackets and clamps of the transfer pipe of the tail tank, and 
of the transfer pipe assembly; and replacement of damaged parts, or 
installation of a doubler, if necessary. This amendment adds a 
requirement to install a fuel transfer pipe of the tail tank, and to 
install support brackets and clamps of the fuel feed pipe of engine No. 
2, which constitutes terminating action for the repetitive inspections. 
This amendment also requires, for certain airplanes, removal of a 
temporary protective doubler installed on the fuel pipe assembly. This 
amendment is prompted by reports of cracking of the support brackets in 
the refuel and fuel transfer lines of the tail fuel tank and damage to 
the nylon clamps and transfer pipe assembly. The actions specified by 
this AD are intended to prevent such cracking and damage, which could 
result in further damage to the transfer pipe assembly and possible 
fuel leakage.

DATES: Effective June 6, 1997.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD11-28A083, dated March 13, 1996, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of May 24, 1996 (61 FR 21066, May 9, 1996).
    The incorporation by reference of certain other publications listed 
in the regulations is approved by the Director of the Federal Register 
as of June 6, 1997.

ADDRESSES: The service information referenced in this AD may be 
obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, 
Long Beach, California 90846, Attention: Technical Publications 
Business Administration, Department 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: Raymond Vakili, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone 
(310) 627-5262; fax (310) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 96-10-07, 
amendment 39-9612 (61 FR 21066, May 9, 1996), which is applicable to 
certain McDonnell Douglas Model MD-11 series airplanes, was published 
in the Federal Register on February 18, 1997 (62 FR 7180). The action 
proposed to supersede AD 96-10-07 to continue to require visual 
inspections to detect cracking, bending, or stress of the support 
brackets and damage to the nylon clamps of the transfer pipe of the 
tail tank. It also proposed to continue to require repetitive 
inspections to detect damage of the support brackets and clamps.
    However, for certain airplanes, this AD adds a requirement to 
remove certain clamps and the temporary protective doubler on the fuel 
pipe assembly. It also requires installation of a fuel transfer pipe of 
the tail tank, and installation of support brackets and pipe clamps of 
the fuel feed pipe on engine No. 2, which constitutes terminating 
action for the repetitive inspections.
    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 145 Model MD-11 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 40 
airplanes of U.S. registry will be affected by this proposed AD.
    The actions that are currently required by AD 96-10-07 take 
approximately 2 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 $4,800, or $120 per airplane, per inspection cycle.
    The new actions that are required by this new AD will take 
approximately 6 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$691 per airplane. Based on these figures, the cost impact of the new 
requirements of this AD on U.S. operators is estimated to be $42,040, 
or $1,051 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)

[[Page 24020]]

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 39-9612 (61 FR 
21066, May 9, 1996), and by adding a new airworthiness directive (AD), 
amendment 39-10003, to read as follows:

97-09-07  McDonnell Douglas: Amendment 39-10003. Docket 96-NM-278-
AD. Supersedes AD 96-10-07, Amendment 39-9612.

    Applicability: Model MD-11 series airplanes; as listed in 
McDonnell Douglas Service Bulletin MD11-28-089, dated October 24, 
1996; 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 (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 prevent cracking of the support brackets in the refuel and 
fuel transfer lines of the tail fuel tank and damage to the nylon 
clamps and transfer pipe assembly, which, if not corrected, could 
result in further damage to the transfer pipe assembly and possible 
fuel leakage, accomplish the following:

Restatement of Requirements of AD 96-10-07

    (a) For Group 1 airplanes listed in McDonnell Douglas Alert 
Service Bulletin MD11-28A083, dated March 13, 1996: Within 90 days 
after May 24, 1996 (the effective date of AD 96-10-07, amendment 39-
9612), accomplish the requirements of paragraphs (a)(1) and (a)(2) 
of this AD in accordance with Paragraph 3. of the Accomplishment 
Instructions of McDonnell Douglas Alert Service Bulletin MD11-
28A083, dated March 13, 1996, or McDonnell Douglas Alert Service 
Bulletin MD11-28A083, Revision 01, dated May 29, 1996.
    (1) Perform a visual inspection for cracking, bending, or stress 
of the support brackets and damage to the nylon clamps of the 
transfer pipe of the tail tank, in accordance with the alert service 
bulletin. If any damaged bracket or clamp is detected, prior to 
further flight, replace it with a serviceable part in accordance 
with the alert service bulletin.
    (2) Perform a visual inspection for chafing and/or denting of 
the transfer pipe assembly of the tail tank, in accordance with the 
alert service bulletin.
    (i) Condition 1. If no damage to the fuel pipe assembly is 
detected, accomplish the requirements of either paragraph 
(a)(2)(i)(A) or (a)(2)(i)(B) of this AD at the times specified in 
that paragraph.
    (A) Condition 1, Option 1. Thereafter, repeat the visual 
inspections required by paragraph (a) of this AD at intervals not to 
exceed 600 flight hours; or
    (B) Condition 1, Option 2. Install a temporary doubler on the 
fuel pipe assembly in accordance with the alert service bulletin 
and, thereafter, repeat the visual inspections required by paragraph 
(a) of this AD at intervals not to exceed 15 months.
    (ii) Condition 2. If damage is found that is within the limits 
specified by the alert service bulletin, prior to further flight, 
install a temporary doubler on the fuel pipe assembly. Thereafter, 
repeat the visual inspections required by paragraph (a) of this AD 
at intervals not to exceed 15 months.
    (iii) Condition 3. If damage is found that is outside the limits 
specified by the alert service bulletin, prior to further flight, 
replace the fuel pipe assembly with a new or serviceable assembly; 
and accomplish the requirements of either paragraph (a)(2)(iii)(A) 
or (a)(2)(iii)(B) of this AD at the time specified in that 
paragraph.
    (A) Condition 3, Option 1. Thereafter, repeat the visual 
inspections required by paragraph (a) of this AD at intervals not to 
exceed 600 flight hours; or
    (B) Condition 3, Option 2. Install a temporary doubler on the 
fuel pipe assembly; and repeat the visual inspections required by 
paragraph (a) of this AD, thereafter, at intervals not to exceed 15 
months. (Replacement of the fuel pipe assembly with a serviceable 
pipe assembly that has been repaired by welding a doubler in the 
area of potential damage, does not require the installation of a 
temporary doubler.)

New Requirements of This AD

    (b) Within 24 months after the effective date of this AD, 
accomplish the requirements of paragraphs (b)(1) and (b)(2) of this 
AD, as applicable.
    (1) For airplanes on which the temporary protective doubler has 
been installed on the fuel pipe assembly in accordance with 
McDonnell Douglas Alert Service Bulletin MD11-28A083, dated March 
13, 1996: Remove the clamps and the temporary protective doubler 
installed on the fuel transfer pipe, in accordance with McDonnell 
Douglas Service Bulletin MD11-28-089, dated October 24, 1996. Prior 
to further flight following accomplishment of the removal, 
accomplish the requirements of paragraph (a)(2) of this AD.
    (2) For all airplanes: Install the fuel transfer pipe of the 
tail tank and support brackets and clamps of the fuel feed pipe of 
engine No. 2, in accordance with McDonnell Douglas Service Bulletin 
MD11-28-089, dated October 24, 1996. Accomplishment of this 
installation constitutes terminating action for the requirements of 
this AD.
    (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, Los Angeles 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, Los Angeles ACO.
    (2) Alternative methods of compliance that concern the use of an 
alternate material in lieu of the specified temporary doubler, which 
were approved previously in accordance with AD 96-10-07, amendment 
39-9612, are not considered to be approved as alternative methods of 
compliance with this AD.
    (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, Los Angeles 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, 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.

    (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.
    (f) Certain actions shall be done in accordance with McDonnell 
Douglas Alert Service Bulletin MD11-28A083, dated March 13, 1996, or 
McDonnell Douglas Alert Service Bulletin MD11-28A083, Revision 01, 
dated May 29, 1996. Certain other actions shall be done in 
accordance with McDonnell Douglas Service Bulletin MD11-28-089, 
dated October 24, 1996. The incorporation by

[[Page 24021]]

reference of McDonnell Douglas Alert Service Bulletin MD11-28A083, 
dated March 13, 1996, 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 May 24, 1996 (61 FR 21066, May 9, 1996). The incorporation 
by reference of the remainder of the service documents listed above 
is 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 
McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Technical Publications Business 
Administration, Department 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.
    (g) This amendment becomes effective on June 6, 1997.

    Issued in Renton, Washington, on April 21, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-10788 Filed 5-1-97; 8:45 am]
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