AD 2001-18-11

[Federal Register Volume 66, Number 179 (Friday, September 14, 2001)]
[Rules and Regulations]
[Pages 47881-47883]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-22996]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-230-AD; Amendment 39-12437; AD 2001-18-11]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model 717 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 717 series airplanes. 
This action requires a one-time inspection of the support seal tubes of 
the rudder trim and load-feel actuator assembly of the rudder trim 
control system, located in the aft accessory compartment, for proper 
clearance between the actuator support seal tube and spring capsule 
assembly, and applicable follow-on/corrective actions. This action is 
necessary to detect and correct the accumulation of moisture in the 
rudder trim and load-feel actuator of the rudder trim control system. 
Such moisture could freeze and cause stiff operation, binding, or 
jamming of the rudder trim control system and consequent jamming of the 
rudder; and adversely affect directional control of an airplane.

DATES: Effective October 1, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 1, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before November 13, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-230-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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#d1e8fcb0bfbcfcb8b0a3b2bebcbcb4bfa591b7b0b0ffb6bea7"><span class="__cf_email__" data-cfemail="2e17034f404303474f5c4d4143434b405a6e484f4f00494158">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-230-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 
Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024). This information may be examined 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the FAA, 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: Albert Lam, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, the FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712; telephone (562) 627-5346; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: The FAA has received several reports of in-
flight binding and/or stiff operation of the rudder trim control system 
on McDonnell Douglas Model 717 series airplanes. Subsequent 
investigation indicates that approximately 60 rudder trim and load-feel 
actuators were manufactured with insufficient clearance between the 
actuator support seal tube and spring capsule assembly, and these 
actuators were installed on Model 717 series airplanes. Moisture 
condensing in the area of those components could freeze and cause stiff 
operation, binding, or jamming of the rudder trim control system. Such 
conditions could result in consequent jamming of the rudder and 
adversely affect directional control of an airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
717-27A0016, including Appendix, dated April 9, 2001, which describes 
procedures for a one-time inspection of the support seal tubes of the 
rudder trim and load-feel actuator assembly of the rudder trim control 
system, located in the aft accessory compartment, for proper clearance 
between the actuator support seal tube and spring capsule assembly, and 
applicable follow-on/corrective actions. The Boeing service bulletin 
refers to BFGoodrich Aerospace Service Bulletin DL4528M1-27-20, dated 
April 3, 2001, as an additional source of service information. The 
inspection and follow-on/corrective actions include the following 
procedures:
    <bullet> Condition 1: For a 5-inch support seal tube, as specified 
in the Boeing service bulletin, reidentify the rudder trim and load-
feel actuator assembly, and apply a nylon or polyurethane clear 
coating.
    <bullet> Condition 2: For a 6-inch support seal tube, as specified 
in the Boeing service bulletin, modify and reidentify the actuator 
assembly, and install the modified and reidentified actuator assembly. 
Modification action includes removing sealant from around the screw 
heads and flange of the support seal tube; removing safety wire from 
screws; removing the support seal tube; cleaning any excess sealant 
compound from the support seal tube, cover, and front cap; applying 
sealing compound to the support tube at certain locations; installing 
and securing a new support seal tube, using six screws having a 
specified torque value and securing them with safety wire; 
reidentifying the actuator identification plate; and applying a clear 
coating to the flange of the support seal tube.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other McDonnell Douglas Model 717 series airplanes 
of the same type design, this AD is being issued to detect and correct 
the accumulation of moisture in the rudder trim and load-feel actuator 
of the rudder trim control system. Such moisture could freeze and 
result in stiff operation, binding, or jamming of the rudder trim 
control system and consequent jamming of the rudder; and adversely 
affect directional control of an airplane.
    This AD requires accomplishment of the actions specified by the 
previously referenced Boeing service bulletin, except as discussed 
below.

Differences Between the Service Information and This AD

    Operators should note that the BFGoodrich Aerospace service 
bulletin, which is referenced by the Boeing service bulletin as an 
additional source of information, specifies the application of a nylon 
or polyurethane clear coating

[[Page 47882]]

``or equivalent.'' However, the FAA has determined that it is necessary 
to specify the use of a nylon or polyurethane clear coating in 
paragraph (a)(1) of this AD.
    Operators also should note that the reporting requirement in 
paragraph (b) of this AD also includes an additional requirement to 
identify whether a 5-inch or a 6-inch support seal tube is found 
installed on the airplane during the inspection required by paragraph 
(a) of this AD.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

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 Number 2001-NM-230-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:

2001-18-11  McDonnell Douglas: Amendment 39-12437. Docket 2001-NM-
230-AD.

    Applicability: Model 717 series airplanes, as listed in Boeing 
Alert Service Bulletin 717-27A0016, including Appendix, dated April 
9, 2001; 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 detect and correct the accumulation of moisture in the rudder 
trim and load-feel actuator of the rudder trim control system, which 
could freeze and cause stiff operation, binding, or jamming of the 
rudder trim control system and consequent jamming of the rudder; and 
adversely affect directional control of an airplane; accomplish the 
following:

Detailed Visual Inspection

    (a) Within 60 days after the effective date of this AD, do a 
one-time detailed visual inspection of the support seal tube of the 
rudder trim and load-feel actuator assembly, located in the aft 
accessory compartment, for proper clearance between the actuator 
support seal tube and spring capsule assembly, per paragraph 3.B. of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
717-27A0016, including Appendix, dated April 9, 2001; and, before 
further flight, accomplish the actions specified in paragraph (a)(1) 
or (a)(2) of this AD, as applicable.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''


    Note 3: The Boeing service bulletin refers to BFGoodrich 
Aerospace Service Bulletin DL4528M1-27-20, dated April 3, 2001, as 
an additional source of service information for accomplishment of 
the one-time detailed visual inspection and follow-on/corrective 
actions.


[[Page 47883]]



Follow-on/Corrective Actions

Condition 1: For a 5-inch Support Seal Tube

    (1) Reidentify the rudder trim and load-feel actuator assembly, 
and apply a nylon or polyurethane clear coating, per Condition 1, 
paragraphs 1 through 3, paragraph 3.B. of the Accomplishment 
Instructions of the service bulletin. Where there are differences 
between the AD and the service information, the AD prevails.

Condition 2: For a 6-inch Support Seal Tube

    (2) Modify (including removing sealant from around the screw 
heads and flange of the support seal tube; removing safety wire from 
screws; removing the support seal tube; cleaning any excess sealant 
compound from the support seal tube, cover, and front cap; applying 
sealing compound to the support tube at certain locations; 
installing and securing a new support seal tube, using six screws 
having a specified torque value and securing them with safety wire; 
reidentifying the actuator identification plate; and applying a 
clear coating to the flange of the support seal tube) and reidentify 
the rudder trim and load-feel actuator assembly; and install the 
modified and reidentified actuator assembly; per Condition 2, 
paragraphs 1 through 14, paragraph 3.B. of the Accomplishment 
Instructions of the service bulletin.

    Note 4: Although the BFGoodrich service bulletin specifies that 
the action for Condition 1 is for a 5.25-inch support seal tube and 
Condition 2 is for a 6.25-inch support seal tube, this AD specifies 
5 inches and 6 inches respectively, as cited in the Boeing service 
bulletin.

Reporting Requirement

    (b) Within 10 days after accomplishing the one-time inspection 
required by paragraph (a) of this AD, submit a report of the 
inspection results (both positive and negative findings) to the 
Manager, Los Angeles Aircraft Certification Office (ACO), FAA, or to 
Boeing, per the Appendix of Boeing Alert Service Bulletin 717-
27A0016, dated April 9, 2001. The report must include the part 
number and serial number of the rudder trim load feel actuator, date 
of inspection, fuselage number, and number of flight hours or flight 
cycles on the airplane. The report also must include whether the 
support seal tube found installed on the airplane during the 
detailed visual inspection required by paragraph (a) of this AD is 5 
inches or 6 inches. Information collection requirements contained in 
this regulation have been approved by the Office of Management and 
Budget (OMP) 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.

Spares

    (c) As of the effective date of this AD, no person shall install 
on any airplane, a support seal tube, part number (P/N) A9543, 
Revision A, on a rudder trim and load-feel actuator, P/N 
DL4528M1MOD5 or P/N DL4528M1MOD6.

Alternative Methods of Compliance

    (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. 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 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (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.

Incorporation by Reference

    (f) The actions shall be done in accordance with Boeing Alert 
Service Bulletin 717-27A0016, including Appendix, dated April 9, 
2001. 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 Boeing Commercial Aircraft 
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the FAA, 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.

Effective Date

    (g) This amendment becomes effective on October 1, 2001.

    Issued in Renton, Washington, on September 4, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-22996 Filed 9-13-01; 8:45 am]
BILLING CODE 4910-13-U