[Federal Register Volume 64, Number 6 (Monday, January 11, 1999)]
[Rules and Regulations]
[Pages 1502-1503]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-480]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-348-AD; Amendment 39-10988; AD 98-25-11 R1]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; correction.
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SUMMARY: This amendment corrects and clarifies information in an
existing airworthiness directive (AD), applicable to all McDonnell
Douglas Model MD-11 series airplanes, that currently requires a one-
time inspection to detect discrepancies at certain areas around the
entry light connector of the sliding ceiling panel above the forward
passenger doors, and repair, if necessary. The actions specified in
that AD are intended to prevent chafing of the electrical wire
assemblies, which could result in an electrical fire in the passenger
compartment. This amendment corrects and clarifies the requirements of
the current AD by specifying the specific area in which the subject
inspection must be conducted and by correcting the part number of the
ramp deflector assembly. This amendment is prompted by communication
received from the manufacturer that the current requirements of the AD
are unclear.
EFFECTIVE DATE: December 28, 1998.
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 December 3, 1998, the FAA issued AD 98-
25-11, amendment 39-10937 (63 FR 68172, December 10, 1998), which is
applicable to all McDonnell Douglas Model MD-11 series airplanes. That
AD requires a one-time inspection to detect discrepancies at certain
areas around the entry light connector of the sliding ceiling panel
above the forward passenger doors, and repair, if necessary. That
action was prompted by a report indicating that damaged electrical
wires were found above the forward passenger doors due to flapper
panels moving inboard and chafing the electrical wire assemblies of
this area. The actions required by that AD are intended to prevent such
chafing, which could result in an electrical fire in the passenger
compartment.
Since the issuance of AD 98-25-11, the FAA has reviewed some of the
wording of that AD and finds that clarification is necessary. The FAA's
intent in paragraph (a) of the AD was that operators perform a visual
inspection ``of the aircraft wiring'' to detect discrepancies of the
subject area. This action revises paragraph (a) of the AD to clarify
this point.
The FAA has determined that the area specified in paragraph (a)(1)
of that AD is not clear in the way that it is currently worded, and
that operators may misinterpret what area needs to be inspected. The
FAA finds that the wording of paragraph (a)(1) must be revised to
specify that a visual inspection must be accomplished ``at the area of
the forward drop ceiling just outboard of mod block S3-735, and forward
and inboard of the light ballast for the entry light on the sliding
ceiling panel above the forward left passenger door (1L) at station
location x = 24.75, y = 435, and z = 64.5.'' In addition, this action
includes a new NOTE 2 following paragraph (a)(1) of the AD to specify
that the clarified area is the same area that was identified in AD 98-
25-11.
In addition, the manufacturer has informed the FAA that bracket
``part number 4225419-1,'' as specified in paragraph (a)(2) of AD 98-
25-11, does not exist. In addition, the FAA finds that the word
``bracket'' does not clearly describe the area in which the required
inspection should be conducted. Therefore, this action revises
paragraph (a)(2) of the AD to read, ``* * * in the area of the ramp
deflector assembly, part number 4223570-501.''
The manufacturer also has informed the FAA that the latest revision
of Chapter 20, Standard Wiring Practices of the MD-11 Wiring Diagram
Manual is dated April 1, 1998. The procedures described in the revision
dated April 1, 1998, are essentially identical to those described in
the revision dated January 1, 1998, which was referenced in AD 98-25-11
as the appropriate source of service information for accomplishment of
the repair requirement. Therefore, this action revises paragraph (b) of
the AD to include Chapter 20, Standard Wiring Practices of the MD-11
Wiring Diagram Manual, dated April 1, 1998, as an additional source of
service information.
Action is taken herein to clarify and correct these requirements of
AD 95-25-11 and to correctly add the AD as an amendment to section
39.13 of the Federal Aviation Regulations (14 CFR 39.13).
The final rule is being reprinted in its entirety for the
convenience of affected operators. The effective date remains December
23, 1998.
[[Page 1503]]
Since this action only clarifies and corrects a current
requirement, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, notice and public
procedures hereon are unnecessary.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Correction
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 39-10937 (63 FR
68172, December 10, 1998), and by adding a new airworthiness directive
(AD), amendment 39-10988, to read as follows:
98-25-11 R1 McDonnell Douglas: Amendment 39-10988. Docket 98-NM-
348-AD. Revises AD 98-25-11, Amendment 39-10937.
Applicability: All Model MD-11 series airplanes, 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 (d) 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 chafing of certain electrical wires above the forward
passenger doors, which could result in an electrical fire in the
passenger compartment, accomplish the following:
(a) Within 10 days after the effective date of this AD, perform
a visual inspection of the aircraft wiring to detect discrepancies
that include but are not limited to frayed, chafed, or nicked wires
and wire insulation in the areas specified in paragraphs (a)(1) and
(a)(2) of this AD.
(1) At the area of the forward drop ceiling just outboard of mod
block S3-735, and forward and inboard of the light ballast for the
entry light on the sliding ceiling panel above the forward left
passenger door (1L) at station location x = 24.75, y = 435, and z =
64.5.
Note 2: The area specified in paragraph (a)(1) of this AD is the
same area that was identified in AD 98-25-11.
(2) At the area above the forward right passenger door (1R) at
station location x = -30, y = 430, and z = 70 in the ramp deflector
assembly part number 4223570-501.
(b) If any discrepancy is detected during the visual inspection
required by paragraph (a) of this AD, prior to further flight,
repair in accordance with Chapter 20, Standard Wiring Practices of
the MD-11 Wiring Diagram Manual, dated January 1, 1998, or April 1,
1998.
(c) Within 10 days after accomplishing the visual inspection
required by paragraph (a) of this AD, submit a report of the
inspection results (both positive and negative findings) to the
Manager, FAA, Transport Airplane Directorate, Los Angeles Aircraft
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood,
California 90712; telephone (562) 627-5350; 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.
(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 3: 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) The effective date of this amendment remains December 28,
1998.
Issued in Renton, Washington, on December 31, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-480 Filed 1-8-99; 8:45 am]
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