[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
