[Federal Register Volume 59, Number 218 (Monday, November 14, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-27967]


[[Page Unknown]]

[Federal Register: November 14, 1994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-NM-202-AD; Amendment 39-9070; AD 93-25-09 R1]

 

Airworthiness Directives; McDonnell Douglas Model MD-11 and DC-10 
Series Airplanes, and Model KC-10A (Military) Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment revises an existing airworthiness directive 
(AD), applicable to certain McDonnell Douglas Model MD-11 and DC-10 
series airplanes, and Model KC-10A (military) airplanes, that currently 
requires repetitive functional testing to verify proper installation of 
the electrical connectors to the engine generator and fire bell shutoff 
switches, and correction of the installation, if necessary; and the 
reporting of findings of discrepancies as a result of the repetitive 
functional tests. That AD was prompted by a report indicating that the 
electrical connectors to the fire extinguishing handles were found to 
be connected incorrectly (crossed) on one airplane. The actions 
specified in that AD are intended to prevent the wrong engine-driven 
generator from being shut down unnecessarily in the event of an engine 
fire or severe damage to the engine. This amendment deletes the 
requirement to submit reports repetitively following each functional 
test.

DATES: Effective November 29, 1994.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of January 7, 1994 (58 FR 68026, December 23, 1993).
    Comments for inclusion in the Rules Docket must be received on or 
before January 13, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-202-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The service information referenced in this AD may be obtained from 
McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 
90801-1771, Attention: Business Unit Manager, Technical Administrative 
Support, Department L51, M.C. 2-98. 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, 3229 East Spring Street, Long Beach, 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-141L, FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3229 East Spring Street, Long 
Beach, California 90806-2425; telephone (310) 988-5262; fax (310) 988-
5210.

SUPPLEMENTARY INFORMATION: On December 16, 1993, the FAA issued AD 93-
25-09, amendment 39-8775 (58 FR 68026, December 23, 1993), which is 
applicable to certain McDonnell Douglas Model MD-11 and DC-10 series 
airplanes, and Model KC-10A (military) airplanes. That AD requires a 
functional test to verify proper installation of the electrical 
connectors to the engine generator and fire bell shutoff switches, and 
correction of the installation, if necessary. A similar functional test 
is required any time that maintenance is performed on the fire 
extinguishing handle system. That AD also requires operators to submit 
to the FAA a report of findings when any discrepancies are identified 
during any of the required functional tests.
    That action was prompted by a report that, during pre-delivery 
testing of a Model MD-11 series airplane, the electrical connectors to 
the fire extinguishing handles were found to be connected incorrectly 
(crossed). The actions required by that AD are intended to prevent the 
wrong engine-driven generator from being shut down unnecessarily in the 
event of an engine fire or severe damage to the engine.
    In response to the reporting requirements of AD 93-25-09, operators 
of Model MD-11 and DC-10 series airplanes, and Model KC-10A (military) 
airplanes have not reported finding any discrepancies as a result of 
the functional tests of the fire extinguishing handle system. 
Therefore, the FAA has determined that it is appropriate to take action 
to revise paragraph (e) of that AD to delete the requirement to report 
the findings of discrepancies as a result of any functional test other 
than the initial one. Submission of a report to the FAA is required 
only after the initial functional test, as required by paragraph (a) of 
the AD.
    Further, the FAA finds that removal of this reporting requirement 
will not compromise safety of the fleet due to the ongoing system of 
reports required by section 121.703 of the Federal Aviation Regulations 
(14 CFR 121.703), ``Mechanical reliability reports.''
    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD 
continues to require a one-time functional test to verify proper 
installation of the electrical connectors to the engine generator and 
fire bell shutoff switches, and correction of the installation, if 
necessary; and a report that details the findings of discrepancies 
identified during the accomplishment of the initial functional test. 
This AD deletes the requirement to report findings of discrepancies as 
a result of the repetitive functional tests of the fire extinguishing 
handle system.
    This AD merely deletes a previously-required action; it requires no 
additional work to be performed by affected operators. In light of 
this, the FAA has determined that it has no adverse economic impact and 
imposes no additional burden on any person. Therefore, notice and 
public procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.
Cost Impact
    There are approximately 526 Model MD-11 and DC-10 series airplanes, 
and Model KC-10A (military) airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 316 airplanes of U.S. registry 
will continue to be affected by the requirements that are retained in 
this AD. To accomplish the actions in this AD, it will take 
approximately 0.5 work hour per airplane, at an average labor rate of 
$55 per work hour. Based on these figures, the total cost impact of the 
AD on U.S. operators is estimated to be $8,690, or $27.50 per airplane.
    Because this AD deletes a previously-required reporting action, it 
eliminates the costs associated with that reporting action. Therefore, 
the economic burden to operators is lessened by that amount.
Comments Invited
    Although this action is in the form of a final rule and was not 
preceded by notice and 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 94-NM-202-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.
    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) 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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-8775 (58 FR 
68026, December 23, 1993), and by adding a new airworthiness directive 
(AD), amendment 39-9070, to read as follows:

93-25-09 R1  McDonnell Douglas: Amendment 39-9070. Docket 94-NM-202-
AD. Revises AD 93-25-09, Amendment 39-8775.

    Applicability: Model MD-11 series airplanes as listed in 
McDonnell Douglas MD-11 Alert Service Bulletin A26-16, dated 
November 22, 1993; and Model DC-10 series airplanes and Model KC-10A 
(military) airplanes as listed in McDonnell Douglas DC-10/KC-10A 
Alert Service Bulletin A26-46, dated December 6, 1993; certificated 
in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent the wrong engine-driven generator from being shut 
down unnecessarily in the event of an engine fire or severe damage 
to the engine, accomplish the following:
    (a) Perform a functional test to verify proper installation of 
the electrical connectors to the engine generator and fire bell 
shutoff switches at the time specified in either paragraph (a)(1) or 
(a)(2) of this AD, as applicable.
    (1) For Model MD-11 series airplanes: Within 30 days after 
January 7, 1994 (the effective date of AD 93-25-09, amendment 39-
8775), in accordance with the Accomplishment Instructions of 
McDonnell Douglas MD-11 Alert Service Bulletin A26-16, dated 
November 22, 1993. Or
    (2) For Model DC-10 series airplanes, and Model KC-10A 
(military) airplanes: Within 60 days after January 7, 1994 (the 
effective date of AD 93-25-09, amendment 39-8775), in accordance 
with the Accomplishment Instructions of McDonnell Douglas DC-10/KC-
10A Alert Service Bulletin A26-46, dated December 6, 1993.
    (b) If the electrical connectors are found to be properly 
installed, no further action is required by paragraph (a) of this 
AD.
    (c) If the electrical connectors are found to be improperly 
installed, prior to further flight, correct the wiring installation 
and repeat the functional test, in accordance with the 
Accomplishment Instructions of McDonnell Douglas MD-11 Alert Service 
Bulletin A26-16, dated November 22, 1993 (for Model MD-11 series 
airplanes); or McDonnell Douglas DC-10/KC-10A Alert Service Bulletin 
A26-46, dated December 6, 1993 [for Model DC-10 series airplanes, 
and Model KC-10A (military) airplanes]; as applicable.
    (d) Prior to further flight following any maintenance performed 
on the fire extinguishing handle system, repeat the functional test 
in accordance with the Accomplishment Instructions of McDonnell 
Douglas MD-11 Alert Service Bulletin A26-16, dated November 22, 1993 
(for Model MD-11 series airplanes); or McDonnell Douglas DC-10/KC-
10A Alert Service Bulletin A26-46, dated December 6, 1993 [for Model 
DC-10 series airplanes and, Model KC-10A (military) airplanes]; as 
applicable.
    (e) Within 10 days after completing the functional test required 
by paragraph (a) of this AD, submit a report of the findings of 
discrepancies to the FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office (ACO), 3229 East Spring 
Street, Long Beach, California 90806-2425; fax (310) 988-5210. 
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.
    (f) 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: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

    (g) 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.
    (h) The functional test shall be done in accordance with 
McDonnell Douglas MD-11 Alert Service Bulletin A26-16, dated 
November 22, 1993 (for Model MD-11 series airplanes); or McDonnell 
Douglas DC-10/KC-10A Alert Service Bulletin A26-46, dated December 
6, 1993 [for Model DC-10 series airplanes, or Model KC-10A 
(military) airplanes]; as applicable. This incorporation by 
reference 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 
January 7, 1994 (58 FR 68026, December 23, 1993). Copies may be 
obtained from McDonnell Douglas Corporation, P.O. Box 1771, Long 
Beach, California 90801-1771, Attention: Business Unit Manager, 
Technical Administrative Support, Department L51, M.C. 2-98. 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, 
3229 East Spring Street, Long Beach, California; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (i) This amendment becomes effective on November 29, 1994.

    Issued in Renton, Washington, on November 7, 1994.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-27967 Filed 11-10-94; 8:45 am]
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