[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]


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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.

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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