[Federal Register Volume 64, Number 80 (Tuesday, April 27, 1999)]
[Rules and Regulations]
[Pages 22544-22548]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-10055]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-87-AD; Amendment 39-11138; AD 99-08-51]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This document published in the Federal Register an amendment
[[Page 22545]]
adopting airworthiness directive (AD) 99-08-51 that was sent previously
to all known U.S. owners and operators of certain McDonnell Douglas
Model MD-11 series airplanes by individual notices. This AD requires
visual inspections under the floorboards in the lower center cargo
compartment at frame 1681 to verify that a certain bracket and a
certain open face nylon clamp are installed to a specific support wire
bundle and to detect damage of the subject wire bundle; repair of
damaged wiring; and installation of certain silicone rubber coated with
a glass cloth protective wrap around the wire bundle, if necessary.
This action is prompted by an incident in which the insulation blanket
between frames 1661 and 1681 in the lower center cargo compartment was
found to be burnt due to a missing wiring harness support bracket/clamp
on the wire bundle at frame 1681. The actions specified by this AD are
intended to ensure that such a wire harness support bracket/clamp is
installed; a missing bracket/clamp could cause the wire bundle to chafe
against the frame, which could result in sparks, smoke, and possible
fire in the lower center cargo compartment.
DATES: Effective May 3, 1999, to all persons except those persons to
whom it was made immediately effective by emergency AD 99-08-51, issued
on April 9, 1999, which contained the requirements of this amendment.
Comments for inclusion in the Rules Docket must be received on or
before June 28, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-87-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
Information pertaining to this amendment 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.
FOR FURTHER INFORMATION CONTACT: Brett Portwood, Aerospace Engineer,
ANM-130L, FAA, Transport Airplane Directorate, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California
90712; telephone (562) 627-5350; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: On April 9, 1999, the FAA issued emergency
AD 99-08-51, which is applicable to certain McDonnell Douglas Model MD-
11 series airplanes.
As part of its practice of re-examining all aspects of the service
experience of a particular aircraft whenever an accident occurs, the
FAA has become aware of an incident in which the insulation blanket
between frames 1661 and 1681 in the lower center cargo compartment was
found to be burnt. This incident occurred on a McDonnell Douglas Model
MD-11 series airplane.
Investigation revealed that a wiring harness (including wires with
a 115 volt alternating current) of the aft cargo loader control unit
was contacting the insulation blanket and rubbing against frame 1681
above stringer R46. A wire was cut, and three other wires were missing
insulation. In addition, frame 1681 had signs of arcing damage.
Furthermore, the exposed moisture barrier material of the insulation
blanket was burnt, and a hole was detected on the insulation blanket
where the wiring harness was chafing against frame 1681. Further
investigation revealed that a wiring harness support bracket/clamp on
the wire bundle at frame 1681 may not have been installed during
production of the airplane.
This incident is not considered to be related to an accident that
occurred off the coast of Nova Scotia involving a McDonnell Douglas
Model MD-11 series airplane. The cause of that accident is still under
investigation.
A missing wiring harness support bracket/clamp on the wire bundle
at frame 1681 could cause the wire bundle to chafe against the frame,
which could result in sparks, smoke, and possible fire in the lower
center cargo compartment.
Other Related Rulemaking
The FAA, in conjunction with Boeing and operators of Model MD-11
series airplanes, is continuing to review all aspects of the service
history of those airplanes to identify potential unsafe conditions and
to take appropriate corrective actions. This airworthiness directive is
one of a series of actions identified during that process. The process
is continuing and the FAA may consider additional rulemaking actions as
further results of the review become available.
Explanation of Requirements of the Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of this same type design, this
airworthiness directive is issued to require a visual inspection to
verify that, under the floorboards in the lower center cargo
compartment at frame 1681, a certain bracket and a certain open face
nylon clamps are installed to a specific support wire bundle. This AD
also requires a visual inspection to detect damage of the subject wire
bundle; repair of damaged wiring; and installation of certain silicone
rubber coated with a glass cloth protective wrap around the subject
wire bundle, if necessary. In addition, this AD requires that operators
submit a report of the inspection results to the FAA. The repairs are
required to be accomplished in accordance with the procedures specified
in Chapter 20-30-01 of the McDonnell Douglas MD-11 Airplane Maintenance
Manual, and Chapter 20-10-01 of the McDonnell Douglas MD-11 Wiring
Diagram Manual.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual notices
issued on April 9, 1999, to all known U.S. owners and operators of
certain McDonnell Douglas Model MD-11 series airplanes. These
conditions still exist, and the AD is hereby published in the Federal
Register as an amendment to section 39.13 of the Federal Aviation
Regulations (14 CFR 39.13) to make it effective to all persons.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ``ADDRESSES.''
All communications received on or before the closing date for comments
will be considered, and this rule may be amended in light of the
comments received. Factual information that supports the commenter's
ideas and suggestions is extremely helpful in evaluating the
effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments,
[[Page 22546]]
in the Rules Docket for examination by interested persons. A report
that summarizes each FAA-public contact concerned with the substance of
this AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed stamped
postcard on which the following statement is made: ``Comments to Docket
Number 99-NM-87-AD.'' The postcard will be date stamped and returned to
the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, is filed, 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, 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:
99-08-51 BOEING: Amendment 39-11138. Docket 99-NM-87-AD.
Applicability: Model MD-11 series airplanes, certificated in any
category; having the following fuselage/factory serial numbers:
------------------------------------------------------------------------
Fuselage No. Serial No.
------------------------------------------------------------------------
532....................................................... 48532
542....................................................... 48565
543....................................................... 48566
544....................................................... 48533
545....................................................... 48549
546....................................................... 48470
547....................................................... 48406
548....................................................... 48504
549....................................................... 48602
551....................................................... 48603
552....................................................... 48571
553....................................................... 48604
554....................................................... 48439
555....................................................... 48605
556....................................................... 48572
558....................................................... 48471
559....................................................... 48573
560....................................................... 48600
562....................................................... 48601
563....................................................... 48633
564....................................................... 48513
566....................................................... 48574
568....................................................... 48575
570....................................................... 48542
572....................................................... 48543
574....................................................... 48576
576....................................................... 48415
579....................................................... 48631
580....................................................... 48544
582....................................................... 48632
583....................................................... 48577
587....................................................... 48545
588....................................................... 48578
589....................................................... 48546
590....................................................... 48743
592....................................................... 48744
594....................................................... 48747
595....................................................... 48748
596....................................................... 48745
597....................................................... 48746
598....................................................... 48749
599....................................................... 48579
600....................................................... 48766
601....................................................... 48768
602....................................................... 48767
603....................................................... 48769
604....................................................... 48754
605....................................................... 48623
607....................................................... 48770
608....................................................... 48753
609....................................................... 48773
610....................................................... 48774
613....................................................... 48755
615....................................................... 48758
616....................................................... 48775
617....................................................... 48776
618....................................................... 48777
619....................................................... 48778
620....................................................... 48779
622....................................................... 48624
623....................................................... 48756
624....................................................... 48780
------------------------------------------------------------------------
Note 1: This AD only affects MD-11 airplanes equipped with a 72-
inch cargo door. MD-11 series airplanes equipped with a 104-inch
cargo door are not subject to the unsafe condition addressed by this
AD due to the configuration of the wire bundles.
Note 2: 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 (c) 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 ensure that a wire harness support bracket/clamp is installed
on the wire bundle at frame 1681, accomplish the following:
(a) Within 15 days after the effective date of this AD: Perform
a one-time visual inspection under the floorboards in the lower
center cargo compartment at frame 1681 (approximately one inch
outboard of longeron R46) to verify that a bracket having part
number P/N 9D0062-3-16-24 (or equivalent), and an open face nylon
clamp having P/N NMC1001-1 or 383-1 (see Figure 1, Item 14/267), are
installed to support wire bundle No. AGS9110.
(1) If the bracket and clamp are installed: Prior to further
flight, perform a visual inspection to detect damage of the subject
wire bundle. If any damage is detected, prior to further flight,
accomplish paragraphs (a)(1)(i) and (a)(1)(ii) of this AD.
(i) Repair in accordance with Chapter 20-30-01 of the McDonnell
Douglas MD-11 Airplane Maintenance Manual. And
(ii) Install a silicone rubber coated with a glass cloth
protective wrap [Douglas Material Specification (DMS) 2109 or
equivalent] around the wire bundle in the area over frame 1681 above
stringer R46 in accordance with Chapter 20-10-01 of the McDonnell
Douglas MD-11 Wiring Diagram Manual.
(2) If the bracket or clamp is not installed: Prior to further
flight, perform a visual inspection to detect damage (i.e., chafing,
damage, or missing wire insulation) of the subject wire bundle.
(i) If no damage is detected: Prior to further flight, install a
silicone rubber coated with a glass cloth protective wrap (DMS 2109
or equivalent) around the wire bundle in the area over frame 1681
above stringer R46 in accordance with Chapter 20-10-01 of the
McDonnell Douglas MD-11 Wiring Diagram Manual.
(ii) If any damage is detected: Prior to further flight,
accomplish the actions required by paragraphs (a)(1)(i) and
(a)(1)(ii) of this AD.
(b) Within 10 days after accomplishing the inspection required
by paragraphs (a) and (a)(1) of this AD, submit a report of the
inspection results (both positive and negative
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findings) to the Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, Transport Airplane Directorate, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; fax (562) 627-5210.
Information collection requirements contained in this regulation
have been approved by the Office of Management and Budget (OMB)
under the provisions of the Paperwork Reduction Act of 1980 (44
U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-
0056.
(c) 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 3: 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.
(e) This amendment becomes effective on May 3, 1999, to all
persons except those persons to whom it was made immediately
effective by emergency AD 99-08-51, issued on April 9, 1999, which
contained the requirements of this amendment.
BILLING CODE 4910-13-U
[[Page 22548]]
[GRAPHIC] [TIFF OMITTED] TR27AP99.031
Issued in Renton, Washington, on April 15, 1999.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-10055 Filed 4-26-99; 8:45 am]
BILLING CODE 4910-13-C
