AD 2001-04-15

[Federal Register Volume 66, Number 44 (Tuesday, March 6, 2001)]
[Rules and Regulations]
[Pages 13414-13416]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-4933]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-26-AD; Amendment 39-12135; AD 2001-04-15]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8-31, DC-8-
32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51, DC-8-52, DC-8-53, DC-
8-55, DC-8-61, DC-8-61F, DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8F-
54, and DC-8F-55 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 DC-8-31, DC-8-32, DC-
8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51, DC-8-52, DC-8-53, DC-8-55, 
DC-8-61, DC-8-61F, DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8F-54, and 
DC-8F-55 series airplanes. This action requires modification of the 
flow control system by rerouting the bleed air ducts to warm the pitot 
tube lines. This action is necessary to prevent the pitot lines from 
freezing, which could result in erroneous or total loss of airspeed 
indications to the flight crew, and consequent loss of control of the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective March 21, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 21, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before May 7, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-26-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
<a href="/cdn-cgi/l/email-protection#5f66723e313272363e2d3c3032323a312b1f393e3e71383029"><span class="__cf_email__" data-cfemail="f0c9dd919e9ddd999182939f9d9d959e84b0969191de979f86">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-26-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in this AD may be obtained from 
National Aircraft Service, Inc., 9133 Tecumseh-Clinton Road, Tecumseh, 
Michigan 49286. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the FAA, Chicago Aircraft Certification Office, 2330 East Devon Avenue, 
Room 323, Des Plaines, Illinois; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Roy Boffo, Aerospace Engineer, Systems 
and Flight Test Branch, ACE-117C, FAA, Chicago Aircraft Certification 
Office, 2350 East Devon Avenue, Room 323, Des Plaines, Illinois 60018; 
telephone (847) 294-7564; fax (847) 294-7834.

SUPPLEMENTARY INFORMATION: The FAA has received reports of erroneous 
airspeed readings, including those from the airspeed indicator and 
Machmeter, after a McDonnell Douglas Model DC-8 series airplane had 
flown through visible moisture. The original airplane design included a 
turbo compressor system. The turbo compressors generated enough heat to 
prevent freezing of any trapped moisture in the lines running from the 
pitot tubes. The turbo compressors were removed during installation of 
Supplemental Type Certificate (STC) ST466CH, which incorporated a flow 
control system that

[[Page 13415]]

uses bleed air from the engines. However, the flow control system did 
not generate enough heat in the area of the pitot tube lines to prevent 
freezing. Frozen pitot lines could generate erroneous or total loss of 
airspeed indications to the flight crew, which could result in loss of 
control of the airplane
    A modification to positively address this unsafe condition was 
subsequently developed, and applicable parts and procedures were 
provided to operators of the affected airplanes. However, a recent 
fleetwide inspection revealed that not all of those airplanes had been 
modified.

Explanation of Relevant Service Information

    National Aircraft Service, Inc., issued Service Bulletin SB-98-
01R1, dated January 26, 1999, which the FAA reviewed and approved. The 
service bulletin describes procedures to modify the flow control system 
by rerouting the bleed air ducts to warm the pitot tube lines. 
Accomplishment of the actions specified in the service bulletin is 
intended to adequately address the identified unsafe condition.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD is 
being issued to prevent the pitot lines from freezing, which could 
result in erroneous or total loss of airspeed indications to the flight 
crew, and consequent loss of control of the airplane. This AD requires 
accomplishment of the actions specified in the service bulletin 
described previously, except as discussed below.

Difference Between AD and Service Bulletin

    The service bulletin recommends the modification within 500 flight 
hours after March 1, 1999; this AD requires the modification within 30 
days after the effective date of this AD. In light of the urgency of 
the unsafe condition and the fact that the revised service bulletin has 
been available to affected operators for nearly two years, the FAA 
finds that the required compliance time represents an appropriate 
interval of time allowable for affected airplanes to continue to 
operate without compromising safety.

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.
    Submit comments using the following format:
    <bullet> Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> Include justification (e.g., reasons or data) for each 
request.
    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 2001-NM-26-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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:

2001-04-15  McDonnell Douglas: Amendment 39-12135. Docket 2001-NM-
26-AD.

    Applicability: The following Model DC-8 series airplanes that 
have been modified in accordance with Supplemental Type Certificate 
(STC) ST466CH, certificated in any category:

[[Page 13416]]



 
 
 
                      DC-8-31                        DC-8-55
                      DC-8-32                        DC-8-61
                      DC-8-33                       DC-8-61F
                      DC-8-41                        DC-8-62
                      DC-8-42                       DC-8-62F
                      DC-8-43                        DC-8-63
                      DC-8-51                       DC-8-63F
                      DC-8-52                       DC-8F-54
                      DC-8-53                       DC-8F-55
 


    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 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 prevent the pitot lines from freezing, which could result in 
erroneous or total loss of airspeed indications to the flight crew, 
and consequent loss of control of the airplane, accomplish the 
following:

Modification

    (a) Within 30 days after the effective date of this AD, modify 
the flow control system to reroute the bleed air ducts, in 
accordance with National Aircraft Service, Inc., Service Bulletin 
SB-98-01R1, dated January 26, 1999.

Alternative Methods of Compliance

    (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, Chicago Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Chicago ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Chicago ACO.

Special Flight Permits

    (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.

Incorporation by Reference

    (d) The actions shall be done in accordance with National 
Aircraft Service, Inc., Service Bulletin SB-98-01R1, dated January 
26, 1999. 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 National Aircraft 
Service, Inc., 9133 Tecumseh-Clinton Road, Tecumseh, Michigan 49286. 
Copies may be inspected at the FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Chicago 
Aircraft Certification Office, 2330 East Devon Avenue, Room 323, Des 
Plaines, Illinois; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (e) This amendment becomes effective on March 21, 2001.

    Issued in Renton, Washington, on February 22, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-4933 Filed 3-5-01; 8:45 am]
BILLING CODE 4910-13-P