Airworthiness Directives; McDonnell Douglas Model DC-8-62, DC-8-63, DC-8-62F, and DC-8-63F Airplanes, 61690-61691 [E6-17421]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 71, Number 202 (Thursday, October 19, 2006)]
[Proposed Rules]
[Pages 61690-61691]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-17421]


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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. 71, No. 202 / Thursday, October 19, 2006 / 
Proposed Rules

[[Page 61690]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26084; Directorate Identifier 2006-NM-063-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8-62, DC-8-
63, DC-8-62F, and DC-8-63F Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain McDonnell Douglas Model DC-8-62, DC-8-63, DC-8-62F, and DC-
8-63F airplanes. This proposed AD would require revising the wiring for 
the engine thrust brake circuit and indicating circuit and other 
specified actions, or rerouting the wiring at plug P1-1762A on the 
electrical power center generator control panel, as necessary. This 
proposed AD results from the determination that the thrust reverser 
systems on these airplanes do not adequately preclude inadvertent 
deployment of the thrust reversers. We are proposing this AD to prevent 
inadvertent deployment of the thrust reversers during takeoff or 
landing, which could result in loss of control of the airplane.

DATES: We must receive comments on this proposed AD by December 4, 
2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service Management, Dept. C1-L5A (D800-0024), for the service 
information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: William Bond, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5253; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
26084; Directorate Identifier 2006-NM-063-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    In April 1992, the FAA issued a document titled ``Criteria for 
Assessing Transport Turbojet Fleet Thrust Reverser Safety.'' This 
document is based upon the premise that no failure of thrust reverser 
components anticipated to occur in service should prevent continued 
safe flight and landing of an airplane. In order to comply with the 
criteria in the document, Boeing recommends incorporating a wiring 
modification of the thrust reverser system on McDonnell Douglas Model 
DC-8-62, DC-8-63, DC-8-62F, and DC-8-63F airplanes. Based upon the 
Boeing safety evaluations, we have determined that the existing thrust 
reverser systems on these airplanes do not adequately preclude 
inadvertent deployment of the thrust reversers. Inadvertent deployment 
of the thrust reversers during takeoff or landing could result in loss 
of control of the airplane.

Relevant Service Information

    We have reviewed McDonnell Douglas DC-8 Service Bulletin 78-95, 
Revision 2, dated March 10, 1971; and Revision 1, dated December 29, 
1970. The service bulletins describe procedures for either revising the 
wiring for the engine thrust brake circuit and indicating circuit and 
doing other specified actions, or rerouting the wiring at plug P1-1762A 
on the electrical power center (EPC) generator control panel, depending 
on the configuration of the airplane. The other specified actions 
include modifying and reidentifying a nameplate and accomplishing the 
adjustment/test of the thrust reverser system. For certain airplanes, 
the other specified actions also include installing a new bracket, 
terminal boards, and clamps.

[[Page 61691]]

Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Difference Between the Proposed AD and Service Bulletin.''

Difference Between the Proposed AD and Service Bulletin

    Although the service bulletins do not recommend a compliance time 
for accomplishing the modification, we have coordinated a compliance 
time of 27 months with Boeing. In developing an appropriate compliance 
time for this proposed AD, we considered not only the manufacturer's 
recommendation, but the degree of urgency associated with addressing 
the subject unsafe condition, the average utilization of the affected 
fleet, and the time necessary to perform the modification. In light of 
all of these factors, we find a compliance time of 27 months for 
completing the required actions to be warranted, in that it represents 
an appropriate interval of time for affected airplanes to continue to 
operate without compromising safety.

Costs of Compliance

    There are about 70 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 45 airplanes of 
U.S. registry. The proposed actions would take between 1 and 5 work 
hours per airplane, depending on airplane configuration, at an average 
labor rate of $80 per work hour. For a certain airplane configuration, 
required parts would cost about $9 per airplane. For a certain other 
airplane configuration, required parts would cost about $2,825 per 
airplane. Based on these figures, the estimated cost of the proposed AD 
for U.S. operators is between $4,005 and $145,125, or between $89 and 
$3,225 per airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

McDonnell Douglas: Docket No. FAA-2006-26084; Directorate Identifier 
2006-NM-063-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by December 
4, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-8-62 and DC-8-
63 airplanes and Model DC-8-62F and DC-8-63F airplanes, certificated 
in any category; as identified in McDonnell Douglas DC-8 Service 
Bulletin 78-95, Revision 2, dated March 10, 1971.

Unsafe Condition

    (d) This AD results from the determination that the thrust 
reverser systems on McDonnell Douglas Model DC-8-62, DC-8-63, Model 
DC-8-62F, and DC-8-63F airplanes do not adequately preclude 
inadvertent deployment of the thrust reversers. We are issuing this 
AD to prevent inadvertent deployment of the thrust reversers during 
takeoff or landing, which could result in loss of control of the 
airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Modification of Engine Thrust Brake Circuitry

    (f) Within 27 months after the effective date of this AD, do the 
applicable action specified in paragraph (f)(1) or (f)(2) of this 
AD, by accomplishing all of the applicable actions specified in the 
Accomplishment Instructions of McDonnell Douglas DC-8 Service 
Bulletin 78-95, Revision 2, dated March 10, 1971; or Revision 1, 
dated December 29, 1970.
    (1) Revise the wiring for the engine thrust brake circuit and 
indicating circuit, and do all other specified actions before 
further flight after revising the wiring.
    (2) Reroute the wiring at plug P1-1762A on the electrical power 
center generator control panel.

Alternative Methods of Compliance (AMOCs)

    (g)(1) The Manager, Los Angeles Aircraft Certification Office, 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

    Issued in Renton, Washington, on October 10, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-17421 Filed 10-18-06; 8:45 am]
BILLING CODE 4910-13-P