[Federal Register Volume 66, Number 77 (Friday, April 20, 2001)]
[Proposed Rules]
[Pages 20218-20220]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-9765]



[[Page 20218]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-395-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-100, -200, -300, -400, 
and -500 Series Airplanes, and Model 747, 757, 767, and 777 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Model 737-100, -200, -300, 
-400, and -500 series airplanes, and Model 747, 757, 767, and 777 
series airplanes. This proposal would require replacing the rudder 
pedal pushrod fasteners for both the captain's and first officer's 
pedal assemblies with new, improved fasteners. This action is necessary 
to prevent loss of rudder control due to improperly torqued fasteners 
that connect the pushrod to the rudder pedal assembly, which could 
result in loss of controllability of the airplane. This action is 
intended to address the identified unsafe condition.

DATES: Comments must be received by June 4, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-395-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: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-395-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 the proposed rule may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Barbara Mudrovich, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 227-2983; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     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.
     For each issue, state what specific change to the proposed 
AD is being requested.
     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 proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-395-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2000-NM-395-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received a report from one operator of a Boeing Model 
737-400 series airplane that, during rollout after landing, the 
captain's right rudder pedal moved to the full travel position when it 
was pushed and did not return to the normal position when it was 
released. The first officer used the pedal to control the rudder and 
nose wheel steering. Investigation revealed that the pushrod was not 
connected to the right rudder pedal assembly. The nut and washer were 
found in the lower forward compartment. The airplane in this incident 
had accumulated 17,600 total flight hours and 7,900 total flight 
cycles. Another operator reported that a pilot felt a loose rudder 
pedal. Investigation revealed that the fastener connecting the pushrod 
to the rudder pedal assembly was loose. The airplane in this incident 
had accumulated 3,012 total flight hours and 2,658 total flight cycles.
    In addition, maintenance inspections of 130 in-service Model 737 
series airplanes found four other loose fasteners. The manufacturer 
reports that a loose nut may allow the bolt to migrate out of its hole 
and block the movement of the adjacent rudder pedal. The bolt could 
also fall out of its hole and disconnect the rudder pedal from the 
pushrod.
    The rudder pedal installation that controls the rudder and nose 
wheel steering on certain Model 737-100, -200, -300, and -500 series 
airplanes, and certain Model 747, 757, 767, and 777 series airplanes, 
is similar in design to that on the affected Model 737-400 series 
airplanes. Therefore, those Model 737-100, -200, -300, and -500 series 
airplanes, and Model 747, 757, 767, and 777 series airplanes, may be 
subject to the same unsafe condition revealed on the affected Model 
737-400 series airplanes.
    This condition, if not corrected, could cause loss of rudder 
control due to improperly torqued fasteners that connect the pushrod to 
the rudder pedal assembly, which could result in loss of 
controllability of the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved the Boeing service bulletins 
listed in the following table:

[[Page 20219]]



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           Service bulletin                 Revision level                Date                    Model
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737-27A1214..........................  1......................  July 1, 1999...........  737-100, -200, -300, -
                                                                                          400, and -500.
747-27A2373..........................  Original...............  June 24, 1999..........  747.
757-27A0129..........................  Original...............  March 25, 1999.........  757.
767-27A0159..........................  Original...............  June 10, 1999..........  767.
777-27A0030..........................  Original...............  April 1, 1999..........  777.
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    The service bulletins listed in the table above describe procedures 
for replacing the rudder pedal pushrod fasteners for both the captain's 
and first officer's pedal assemblies with new, improved fasteners. 
Replacement action specifies using self-locking, castellated nuts and 
cotter pins through the bolts for nut retention. Accomplishment of the 
actions specified in the service bulletins is intended to adequately 
address the identified unsafe condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletins described previously.

Cost Impact

    There are approximately 6,097 Model 737-100, -200, -300, -400, and 
-500 series airplanes, and Model 747, 757, 767, and 777 series 
airplanes of the affected design in the worldwide fleet. The FAA 
estimates that 2,338 series airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 1 work 
hour per airplane to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $75 per airplane. Based on these figures, the cost impact 
of the proposed AD on U.S. operators is estimated to be $315,630, or 
$135 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this proposed AD were not adopted. The cost impact 
figures discussed in AD rulemaking actions represent only the time 
necessary to perform the specific actions actually required by the AD. 
These figures typically do not include incidental costs, such as the 
time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.

Regulatory Impact

    The regulations proposed herein 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. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this 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) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Boeing: Docket 2000-NM-395-AD.

    Applicability: Model 737-100, -200, -300, -400, and -500 series 
airplanes, and Model 747, 757, 767, and 777 series airplanes, as 
listed in the following applicable Boeing service bulletin specified 
in the following table; certificated in any category:

                                     Table 1.--Applicable Service Bulletins
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               Model                    Service bulletin         Revision level                 Date
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737-100, -200, -300, -400, and -500  737-27A1214...........  1....................  July 1, 1999.
747................................  747-27A2373...........  Original.............  June 24, 1999.
757................................  757-27A0129...........  Original.............  March 25, 1999.
767................................  767-27A0159...........  Original.............  June 10, 1999.
777................................  777-27A0030...........  Original.............  April 1, 1999.
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    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 (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 loss of rudder control due to improperly torqued 
fasteners that connect the pushrod to the rudder pedal assembly, 
which could result in loss of controllability of the airplane, 
accomplish the following:

[[Page 20220]]

Replacement

    (a) Within 18 months after the effective date of this AD: 
Replace the rudder pedal pushrod fasteners for both the captain's 
and first officer's pedal assemblies with new, improved fasteners 
that use self-locking, castellated nuts and cotter pins through the 
bolts for nut retention, per the applicable Boeing service bulletin 
listed in the following table:

                                     Table 2.--Applicable Service Bulletins
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               Model                    Service bulletin         Revision level                 Date
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737-100, -200, -300, -400, and -500  737-27A1214...........  1....................  July 1, 1999.
747................................  747-27A2373...........  Original.............  June 24, 1999.
757................................  757-27A0129...........  Original.............  March 25, 1999.
767................................  767-27A0159...........  Original.............  June 10, 1999.
777................................  777-27A0030...........  Original.............  April 1, 1999.
----------------------------------------------------------------------------------------------------------------


    Note 2: Replacement actions that include replacing the rudder 
pedal pushrod fasteners for both the captain's and first officer's 
pedal assemblies with new, improved fasteners, which use self-
locking, castellated nuts and cotter pins through the bolts for nut 
retention, accomplished before the effective date of this amendment, 
per Boeing Alert Service Bulletin 737-27A1214, dated April 8, 1999, 
is considered acceptable for compliance with the applicable action 
specified in this amendment.

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, Seattle 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, Seattle ACO.


    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permit

    (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.

    Issued in Renton, Washington, on April 13, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-9765 Filed 4-19-01; 8:45 am]
BILLING CODE 4910-13-P