[Federal Register Volume 63, Number 117 (Thursday, June 18, 1998)]
[Rules and Regulations]
[Pages 33246-33248]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-16047]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-156-AD; Amendment 39-10600; AD 98-13-12]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737, 747, 757, 767, and 
777 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 Boeing Model 737, 747, 757, 767, and 777 
series airplanes. This action requires a one-time inspection to detect 
discrepancies of the fasteners that connect the pushrods to the rudder 
pedal assemblies; and corrective actions, if necessary. This amendment 
is prompted by reports of loose and missing fasteners due to incorrect 
installation. The actions specified in this AD are intended to prevent 
loss of rudder control, jamming of the rudder system, uncommanded 
movement of the rudder system, and consequent reduced controllability 
of the airplane, due to loose or missing fasteners that connect the 
pushrods to the rudder pedal assemblies.

DATES: Effective July 6, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 6, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before August 17, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-156-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The service information referenced in this AD 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; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: R.C. Jones, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Transport Airplane 
Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue, 
SW., Renton, Washington 98055-4056; telephone (425) 227-1118; fax (425) 
227-1181.

SUPPLEMENTARY INFORMATION: The FAA has received a report from an 
operator indicating that, on a Boeing Model 737-400 series airplane, 
during rollout after landing, the captain's right rudder pedal moved to 
the full travel position when it was pushed. The pedal failed to return 
to its normal position after it was released even though the rudder 
remained at the neutral position. Consequently, the first officer used 
his rudder pedals to control the rudder and the nose wheel steering. 
Investigation revealed that the forward end of the pushrod on the right 
rudder pedal was not connected to the rudder pedal assembly. The nut 
and washer of the pushrod were found in the lower forward compartment. 
This airplane had accumulated 17,600 total flight hours and 7,900 total 
flight cycles. A second 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.
    In addition, on a Boeing Model 737-500 series airplane, a nut that 
connects the pushrod to the rudder pedal assembly was loose. This 
airplane had accumulated 3,012 total flight hours and 2,658 total 
flight cycles. Maintenance inspections of 130 in-service Boeing Model 
737 series airplanes revealed four other loose fasteners.
    The cause of the loose and missing nuts and bolts has been 
attributed to incorrect installation of the fasteners that connect the 
pushrods to the rudder pedal assemblies during manufacture. If the nut 
is not installed correctly, the bolt can fall out or may be able to 
move far enough to touch the opposite rudder pedal assembly. These 
conditions, if not corrected, could result in potential loss of rudder 
control, jamming of the rudder system, uncommanded movement of the 
rudder system, and consequent reduced controllability of the airplane.
    The rudder pedal assemblies on certain Boeing Model 747, 757, 767, 
and 777 series airplanes are similar in design to those on the affected 
Model 737 series airplanes. Therefore, the rudder pedal assemblies on 
all of these models may have been installed incorrectly. Consequently, 
all of these models may be subject to the same unsafe condition.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletins 
737-27A1212, 747-27A2368, 757-27A0128, 767-27A0156, and 777-27A0029, 
all dated March 26, 1998. These alert service bulletins describe 
procedures for a one-time inspection to detect discrepancies of the 
fasteners (nuts, bolts, and washers) that connect the forward ends of 
the pushrods to the rudder pedal assemblies; and corrective actions, if 
necessary. Corrective actions include tightening nuts and bolts to 
specified torque limits, installing missing fasteners, and replacing 
incorrectly installed fasteners with new fasteners.

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 loss of rudder control, jamming of the rudder 
system, uncommanded movement of the rudder system, and consequent 
reduced controllability of the airplane, due to loose or missing 
fasteners that connect the pushrods to the rudder pedal assemblies. 
This AD requires accomplishment of the actions specified in the alert 
service bulletins described previously. This AD also requires that 
operators report results of findings of discrepancies to the FAA and to 
Boeing.

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.

[[Page 33247]]

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 98-NM-156-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.
    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:

98-13-12  Boeing: Amendment 39-10600. Docket 98-NM-156-AD.

    Applicability: Model 737, 747, 757, 767, and 777 series 
airplanes; as listed in Boeing Alert Service Bulletins 737-27A1212, 
747-27A2368, 757-27A0128, 767-27A0156, and 777-27A0029; all dated 
March 26, 1998; 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 (c) 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, jamming of the rudder system, 
uncommanded movement of the rudder system, and consequent reduced 
controllability of the airplane, due to loose or missing fasteners 
that connect the pushrods to the rudder pedal assemblies, accomplish 
the following:
    (a) Within 90 days after the effective date of this AD, perform 
a one-time inspection to detect discrepancies of the fasteners that 
connect the forward ends of the pushrods to the rudder pedal 
assemblies; in accordance with Boeing Alert Service Bulletin 737-
27A1212, 747-27A2368, 757-27A0128, 767-27A0156, or 777-27A0029, all 
dated March 26, 1998, as applicable.
    (1) If no discrepancy is detected, no further action is required 
by this AD.
    (2) If any discrepancy is detected, prior to further flight, 
perform the applicable corrective action in accordance with the 
applicable alert service bulletin.
    (b) Submit a report of inspection findings (discrepant findings 
only) to the Manager, Seattle Aircraft Certification Office (ACO), 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; fax (425) 227-1181; and to the Boeing 
Commercial Airplane Group, Attention: Manager, Airline Support, P.O. 
Box 3707, Seattle, Washington 98124-2207; at the applicable time 
specified in paragraph (b)(1) or (b)(2) of this AD. The report must 
include a description of any discrepancy found, the airplane serial 
number, and the total number of landings and flight hours 
accumulated on the airplane. Discrepant findings include, but are 
not limited to, loose or missing fasteners, inadequately torqued 
fasteners, and fasteners incorrectly installed on the pedal 
assemblies or pushrod bearing surfaces. 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.
    (1) For airplanes on which the inspection is accomplished after 
the effective date of this AD: Submit the report within 10 days 
after performing the inspection required by paragraph (a) of this 
AD.
    (2) For airplanes on which the inspection has been accomplished 
prior to the effective date of this AD: Submit the report within 10 
days after the effective date of this AD.
    (c) 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 ACO. 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

    (d) 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.
    (e) The actions shall be done in accordance with:
     Boeing Alert Service Bulletin 737-27A1212, dated March 
26, 1998;
     Boeing Alert Service Bulletin 747-27A2368, dated March 
26, 1998;
     Boeing Alert Service Bulletin 757-27A0128, dated March 
26, 1998;
     Boeing Alert Service Bulletin 767-27A0156, dated March 
26, 1998; or
     Boeing Alert Service Bulletin 777-27A0029, dated March 
26, 1998.
    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 Airplane 
Group, P.O. Box 3707, Seattle, Washington 98124-

[[Page 33248]]

2207. Copies may be inspected at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (f) This amendment becomes effective on July 6, 1998.

    Issued in Renton, Washington, on June 11, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-16047 Filed 6-17-98; 8:45 am]
BILLING CODE 4910-13-U