[Federal Register Volume 62, Number 32 (Tuesday, February 18, 1997)]
[Proposed Rules]
[Pages 7180-7182]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-3842]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 62, No. 32 / Tuesday, February 18, 1997 /
Proposed Rules
[[Page 7180]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-278-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of 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 action
would add 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 action would also require, for certain
airplanes, removal of a temporary protective doubler installed on the
fuel pipe assembly. This action 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 the proposed 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: Comments must be received by March 28, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-278-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule 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 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.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 96-NM-278-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 96-NM-278-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On May 1, 1996, the FAA issued AD 96-10-07, amendment 39-9612 (61
FR 21066, May 9, 1996), applicable to certain McDonnell Douglas Model
MD-11 series airplanes, to require repetitive visual inspections for
cracking, bending, or stress of the support brackets, and any damage to
the clamps of the transfer pipe of the tail tank; and replacement of
any damaged bracket or clamp with a serviceable part. That action also
requires repetitive visual inspections for damage of the transfer pipe
assembly of the tail tank; and installation of a doubler on the pipe
assembly, or replacement of the pipe assembly with a serviceable
assembly, if necessary. That action was 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; such damage is due to flexing of the brackets and subsequent
contact of the transfer pipe assembly with adjacent structure. The
requirements of that AD are intended to prevent such cracking and
damage, which could result in further damage to the transfer pipe
assembly and possible fuel leakage.
In the preamble to AD 96-10-07, the FAA indicated that the actions
required by that AD were considered ``interim action'' and that further
rulemaking was being considered. The FAA now has determined that
further rulemaking action is indeed necessary, and this proposed AD
follows from that determination.
Actions Since Issuance of Previous Rule
Since the issuance of that AD, McDonnell Douglas has developed a
modification procedure that involves installing a fuel transfer pipe of
the tail tank and installing additional support brackets and pipe
clamps of the fuel feed pipe of engine No. 2. Installation of
additional support brackets and pipe
[[Page 7181]]
clamps will positively address the unsafe condition by minimizing the
possibility of fuel pipe damage due to flexing of the brackets and
subsequent contact of the transfer pipe assembly with adjacent
structure.
Explanation of Relevant Service Information
The FAA has reviewed and approved McDonnell Douglas Service
Bulletin MD11-28-089, dated October 24, 1996, which describes
procedures for removal of certain clamps and the temporary protective
doubler on the fuel pipe assembly, if those parts have been installed
previously. The service bulletin also describes procedures for
installing a fuel transfer pipe of the tail tank, and installing
support brackets and pipe clamps of the fuel feed pipe of engine No. 2,
which eliminates the need for repetitive inspections to detect damage
of the support brackets and clamps.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would supersede AD 96-10-07. It would 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 would continue to require repetitive inspections
to detect damage of the support brackets and clamps.
However, for certain airplanes, this new proposed AD would add a
requirement to remove certain clamps and the temporary protective
doubler on the fuel pipe assembly. It also would require installation
of a fuel transfer pipe of the tail tank, and installation of support
brackets and pipe clamps of the fuel feed pipe of engine No. 2, which
constitutes terminating action for the repetitive inspections. These
actions would be required to be accomplished in accordance with
McDonnell Douglas Service Bulletin MD11-28-089, as described
previously.
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 would 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 proposed in this AD action would take
approximately 6 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts would cost
approximately $691 per airplane. Based on these figures, the cost
impact of the proposed 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 current or proposed
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 proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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),
to read as follows:
McDonnell Douglas: 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 Service Bulletin
MD11-28A083, Revision 1, dated May 5, 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
[[Page 7182]]
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.
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.
(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.
Issued in Renton, Washington, on February 10, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-3842 Filed 2-14-97; 8:45 am]
BILLING CODE 4910-13-U
