[Federal Register Volume 61, Number 110 (Thursday, June 6, 1996)]
[Rules and Regulations]
[Pages 28736-28738]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-14037]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-56-AD; Amendment 39-9652; AD 96-12-10]
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 amendment adopts a new airworthiness directive (AD) that 
is applicable to certain McDonnell Douglas Model MD-11 series 
airplanes. This action requires either the application of a vapor 
sealant on the back of the receptacle of the auxiliary power unit (APU) 
power feeder cable; or a visual inspection for gold-plating and 
evidence of damage of the connector contacts of the power feeder cable 
of the APU generator, and various follow-on actions. This amendment is 
prompted by reports of burning and arcing of these connector contacts. 
The actions specified in this AD are intended to reduce the potential 
for a fire hazard as a result of such burning or arcing.

DATES: Effective June 21, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 21, 1996.
    Comments for inclusion in the Rules Docket must be received on or 
before August 5, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 96-NM-56-AD, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056.
    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 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.

FOR FURTHER INFORMATION CONTACT: Brett Portwood, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Transport Airplane 
Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount 
Boulevard, Lakewood, California 90712; telephone (310) 627-5347; fax 
(310) 627-5210.

SUPPLEMENTARY INFORMATION: The FAA has received several reports of 
burning and arcing of the connector contacts (pins/sockets) of the 
power feeder cable of the auxiliary power unit (APU) generator on Model 
MD-11 series airplanes. This condition was indicated by the inability 
to electrically power the airplane using APU generator power. In all 
cases, the connector and receptacle were heat-damaged beyond repair. 
The associated power feeder cables also sustained heat damage. 
Investigation revealed that the connector contacts had been nickel 
plated during production. These connector contacts must be gold plated 
to be able to withstand the loads applied. Burning and arcing of the 
connector contacts of the power feeder cable of the APU generator, if 
not corrected, could result in potential fire hazard.

[[Page 28737]]

Explanation of Relevant Service Information

    The FAA has reviewed and approved McDonnell Douglas Alert Service 
Bulletin MD11-24A104, dated May 7, 1996, which describes procedures for 
application of a vapor sealant on the back of the receptacle of the APU 
power feeder cable. Applying the vapor sealant will reduce the 
possibility of fire or burning until the remainder of the actions 
specified in the alert service bulletin can be accomplished.
    The alert service bulletin also describes procedures for a one-time 
visual inspection for color (gold plating) and evidence of damage of 
the connector contacts (pins/sockets) of the power feeder cable of the 
APU generator located in the upper left corner of the APU compartment 
in the forward bulkhead. It also describes procedures for replacement 
of damaged pins and sockets with gold-plated pins and sockets, or 
deactivation of the electrical operation of the APU until such 
replacement is accomplished. The alert service bulletin specifies that 
the visual inspection and replacement or deactivation (if necessary) 
actions eliminate the need for applying a vapor sealant.
    Additionally, the alert service bulletin describes procedures for 
eventual replacement of undamaged pins and sockets that are nickel-
plated or made of copper (brass), with gold-plated pins and sockets.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Model MD-11 series airplanes of the same type 
design, this AD is being issued to reduce the potential for a fire 
hazard as a result of burning and arcing of the connector contacts of 
the power feeder cable of the APU generator. This AD requires either:
    1. The application of a vapor sealant on the back of the receptacle 
of the APU power feeder cable; or
    2. A one-time visual inspection for color (gold-plating) and 
evidence of damage of the connector contacts (pins/sockets) of the 
power feeder cable of the APU generator; and either replacement of 
damaged pins and sockets with gold-plated pins and sockets, or 
deactivation of the electrical operation of the APU until such 
replacement is accomplished.
    The actions are required to be accomplished in accordance with the 
alert service bulletin described previously.
    This AD is considered to be interim action. The FAA may consider 
further rulemaking action to require operators who install the vapor 
sealant to eventually accomplish the one-time visual inspection (and 
follow-on actions) and the replacement of nickel-plated or copper 
(brass) pins and sockets with gold-plated pins and sockets. However, 
the compliance time that the FAA is considering for accomplishment of 
those actions are sufficiently long so that prior notice and time for 
public comment will be practicable.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

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, 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 96-NM-56-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, if 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, 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:

96-12-10  McDonnell Douglas: Amendment 39-9652. Docket 96-NM-56-AD.

    Applicability: Model MD-11 series airplanes; as listed McDonnell 
Douglas Alert Service Bulletin MD11-24A104, dated May 7, 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

[[Page 28738]]

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 (b) 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 reduce the potential for a fire hazard as a result of burning 
and arcing of the connector contacts of the power feeder cable of 
the auxiliary power unit (APU) generator, accomplish the following:
    (a) Within 60 days after the effective date of this AD, 
accomplish the actions specified in either paragraph (a)(1) or 
(a)(2) of this AD:
    (1) Apply a vapor sealant on the back of the APU power feeder 
cable receptacle in accordance with McDonnell Douglas Alert Service 
Bulletin MD11-24A104, dated May 7, 1996. Or
    (2) Accomplish the actions specified in both paragraph (a)(2)(i) 
and (a)(2)(ii) of this AD in accordance with McDonnell Douglas Alert 
Service Bulletin MD11-24A104, dated May 7, 1996.
    (i) Perform a one-time visual inspection for color (gold-
plating) and evidence of damage of the connector contacts (pins/
sockets) of the power feeder cable of the APU generator located in 
the upper left corner of the APU compartment in the forward 
bulkhead; and
    (ii) Replace any damaged pin or socket with a gold-plated pin or 
socket, or deactivate the electrical operation of the APU until such 
replacement is accomplished.
    (b) 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.

    (c) 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.
    (d) The actions shall be done in accordance with McDonnell 
Douglas Alert Service Bulletin MD11-24A104, dated May 7, 1996. 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 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.
    (e) This amendment becomes effective on June 21, 1996.

    Issued in Renton, Washington, on May 30, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-14037 Filed 6-05-96; 8:45 am]
BILLING CODE 4910-13-P