[Federal Register Volume 64, Number 152 (Monday, August 9, 1999)]
[Rules and Regulations]
[Pages 43051-43053]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-20060]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-180-AD; Amendment 39-11243; AD 99-16-08]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Boeing Model 747-400 series airplanes. This
action requires repetitive inspections of the doubler on the upper
rudder pedal cover to determine whether it is securely bonded to the
upper rudder pedal cover, and corrective action, if necessary. For
airplanes on which the doubler is securely attached to the upper rudder
pedal cover, this AD also provides for installation of two rivets to
retain the doubler, as an optional terminating action for the
repetitive inspections. This amendment is prompted by reports that a
disbonded doubler interfered with rudder pedal movement. The actions
specified in this AD are intended to detect and correct disbonding of
the doubler on the upper rudder pedal cover, which could result in
restricted rudder pedal movement and reduced controllability of the
airplane.
DATES: Effective August 24, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 24, 1999.
Comments for inclusion in the Rules Docket must be received on or
before October 8, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-180-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 indicating
that a disbonded doubler on the upper rudder pedal cover interfered
with the rudder pedal arm. The loose doubler restricted rudder pedal
travel to about one-third of the normal limits. The doubler disbonding
may have been caused by a manufacturing problem. This condition, if not
corrected, could result in restricted rudder pedal movement and reduced
controllability of the airplane.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
747-27A2378, dated July 15, 1999, which describes procedures for
repetitive inspections of the doubler on the upper rudder pedal cover
to determine
[[Page 43052]]
whether it is securely bonded to the upper rudder pedal cover. If the
doubler is securely attached to the upper rudder pedal cover, the alert
service bulletin recommends performing repetitive inspections every 500
flight hours until 2 rivets are installed in the doubler, which
provides secondary retention for the doubler and eliminates the need
for the repetitive inspections. For airplanes where the doubler is not
securely attached to the upper rudder pedal cover, the alert service
bulletin recommends removal of the doubler from the upper rudder pedal
cover, and corrective action within 10 operating days. One method of
corrective action is to repair by bonding a new or serviceable doubler
to the upper rudder pedal cover, and installing 2 rivets in the
doubler, which eliminates the need for the recommended actions of the
alert service bulletin. Another method of corrective action is to
replace the upper rudder cover assembly with a modified upper rudder
cover assembly that has 2 rivets installed in the doubler on the upper
rudder pedal cover. Installation of the modified upper rudder cover
assembly eliminates the need for the recommended actions of the alert
service bulletin. Accomplishment of the actions specified in the alert
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 detect and correct disbonding of the doubler on the
upper rudder pedal cover, which could result in restricted rudder pedal
movement and reduced controllability of the airplane. This AD requires
repetitive inspections of the doubler on the upper rudder pedal cover
to determine whether it is securely bonded to the upper rudder pedal
cover, and corrective action, if necessary. For airplanes on which the
doubler is securely attached to the upper rudder pedal cover, this AD
also provides for installation of two rivets to retain the doubler as
an optional terminating action for the repetitive inspections. The
actions are required to be accomplished in accordance with the alert
service bulletin described previously, except as discussed below.
Differences Between This AD and Alert Service Bulletin
Operators should note that the alert service bulletin recommends
installation of rivets in the doubler on the upper rudder pedal cover
within 5,000 flight hours; however, that action is considered optional
in this AD. The FAA is considering further rulemaking action to require
installation of rivets in the doubler on the upper rudder pedal cover.
However, the planned compliance time to require installation of the
rivets is sufficiently long so that prior notice and time for public
comment will be practicable.
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.
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 99-NM-180-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:
99-16-08 Boeing: Amendment 39-11243. Docket 99-NM-180-AD.
Applicability: Model 747-400 series airplanes, as listed in
Boeing Alert Service Bulletin 747-27A2378, dated July 15, 1999;
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
[[Page 43053]]
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 (e) 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 disbonding of the doubler on the
upper rudder pedal cover, which could result in restricted rudder
pedal movement and reduced controllability of the airplane,
accomplish the following:
Inspection
(a) Within 500 flight hours after the effective date of this AD,
perform an inspection of the doubler on the upper rudder pedal cover
to determine whether the doubler is securely attached to the upper
rudder pedal cover, in accordance with Boeing Alert Service Bulletin
747-27A2378, dated July 15, 1999. If the doubler is securely
attached to the upper rudder pedal cover, repeat the inspection at
intervals not to exceed 500 flight hours.
Corrective Action
(b) If the doubler is not securely attached to the upper rudder
pedal cover during the inspections specified by paragraph (a) of
this AD, prior to further flight, remove the doubler from the upper
rudder pedal cover in accordance with Boeing Alert Service Bulletin
747-27A2378, dated July 15, 1999. Within 10 operating days after
removal of the doubler, accomplish the requirements of paragraph
(b)(1) or (b)(2) of this AD, in accordance with the alert service
bulletin.
Note 2: Operation of the airplane is allowed for a period of 10
operating days with the doubler removed from the upper rudder pedal
cover.
(1) Repair by bonding the doubler to the upper rudder pedal
cover and installing 2 rivets in the doubler. This constitutes
terminating action for the requirements of this AD.
(2) Replace the upper rudder pedal cover assembly with a
modified upper rudder pedal cover assembly having part number
253U3401-15 through -18, as applicable. Such replacement constitutes
terminating action for the requirements of this AD.
Spares
(c) As of the effective date of this AD, no person shall install
an upper rudder pedal cover assembly having part number 253U3401-7,
253U3401-10, 253U3401-11 or 253U3401-13.
Optional Terminating Action
(d) Installation of 2 rivets in the doubler on the upper rudder
pedal cover in accordance with Boeing Alert Service Bulletin 747-
27A2378, dated July 15, 1999, constitutes terminating action for the
repetitive inspections of paragraph (a) of this AD.
Alternative Methods of Compliance
(e) 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, Transport Airplane Directorate. 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 Permits
(f) Special flight permits may be issued in accordance with
sections Secs. 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
(g) The inspections and repairs shall be done in accordance with
Boeing Alert Service Bulletin 747-27A2378, dated July 15, 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 Boeing Commercial Airplane Group,
P.O. Box 3707, Seattle, Washington 98124-2207. 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.
(h) This amendment becomes effective on August 24, 1999.
Issued in Renton, Washington, on July 29, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-20060 Filed 8-6-99; 8:45 am]
BILLING CODE 4910-13-U
