[Federal Register Volume 68, Number 167 (Thursday, August 28, 2003)]
[Proposed Rules]
[Pages 51735-51737]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-22001]
[[Page 51735]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-173-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400, -400D, and -400F
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 Boeing Model 747-400, -
400D, and -400F series airplanes. This proposal would require reviewing
airplane maintenance records; inspecting the yaw damper actuator
portion of the upper and lower rudder power control modules (PCM) for
cracking, and replacing the PCMs if necessary; and reporting airplane
maintenance records review and inspection results to the manufacturer.
This action is necessary to detect and correct cracking in the yaw
damper actuator portion of the upper and lower rudder PCMs, which could
result in an uncommanded left rudder hardover, consequent increased
pilot workload, and possible runway departure upon landing. This action
is intended to address the identified unsafe condition.
DATES: Comments must be received by September 29, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-173-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 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. 2003-NM-173-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 or 2000 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: Doug Tsuji, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6487; fax (425) 917-6590.
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:
[sbull] 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.
[sbull] For each issue, state what specific change to the proposed
AD is being requested.
[sbull] 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 2003-NM-173-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. 2003-NM-173-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received a report that the lower rudder of a Boeing
Model 747-400 series airplane made an uncommanded move to the full left
position (hardover) during flight. The flight crew used lateral and
upper rudder controls to compensate for the lower rudder hardover. The
flight crew used these controls and differential engine thrust to land
the airplane. Investigation revealed that the yaw damper actuator
portion of the lower rudder power control module (PCM) manifold was
broken. The broken manifold is attributed to fatigue cracking in the
lower rudder PCM, which caused the yaw damper to move out of its
correct position and generate the uncommanded lower rudder hardover. An
uncommanded left rudder hardover could result in increased pilot
workload and possible runway departure upon landing.
The upper rudder PCM has the same design as the lower rudder PCM
and can fail in the same manner. An upper rudder PCM failure will
result in an upper rudder surface hardover to the left and would create
a similar unsafe condition as for a failure of the lower rudder PCM.
The PCM part numbers installed on the 747-400D and 747-400F series
airplanes are the same part numbers installed on the affected Model
747-400 series airplane. Therefore those airplanes may be subject to
the unsafe condition identified on the Model 747-400 series airplane.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
747-27A2397, dated July 24, 2003. This service bulletin describes the
following procedures:
[sbull] Reviewing airplane maintenance records to determine if each
PCM has a main manifold with less than 15,000 total flight hours or
2,000 total flight cycles.
[sbull] Performing ultrasonic inspections for cracking of the yaw
damper actuator portion of upper and lower rudder PCMs that have 15,000
or more total flight hours and 2,000 or more total flight cycles.
[sbull] Recording the results of the ultrasonic inspections and
reporting them to Boeing.
[sbull] Replacing subject PCMs that have evidence of possible
cracking.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or
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develop on other products of this same type design, the proposed AD
would require accomplishment of the actions specified in the service
bulletin described previously, except as discussed below.
Differences Between This Proposed AD and the Service Bulletin
The Boeing service bulletin recommends accomplishing the review of
airplane maintenance records and ultrasonic inspection within 6 months
of the issue date of the service bulletin. We have determined that that
interval would address the identified unsafe condition soon enough to
ensure an adequate level of safety for the affected fleet. In
developing an appropriate compliance time for this AD, we considered
the 6-month compliance time recommended by the manufacturer, as well as
the time required for the rulemaking process. In consideration of these
factors, we find that 3 months after the effective date of this final
rule will fall approximately at the same time for compliance as
recommended by the manufacturer. We find that a 3-month compliance time
represents an appropriate interval of time for affected airplanes to
continue to operate without compromising safety.
Interim Action
We consider this proposed AD interim action. The inspection reports
that are required by this AD will enable the manufacturer and the FAA
to obtain better insight into the nature, cause, and extent of the
cracking, and eventually to develop final action to address the unsafe
condition. Once final action has been identified, we may consider
further rulemaking.
Changes to 14 CFR Part 39/Effect on the Proposed AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance (AMOCs). Because we have now included this material in part
39, only the office authorized to approve AMOCs is identified in each
individual AD.
Change to Labor Rate Estimate
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
Cost Impact
There are approximately 180 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 13 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 airplane
maintenance records review, at an average labor rate of $65 per work
hour. Based on these figures, the cost impact of the proposed airplane
maintenance records review on U.S. operators is estimated to be $845,
or $65 per airplane.
Should an operator be required to accomplish the inspection, it
would take approximately 4 work hours per airplane, at an average labor
rate of $65 per work hour. Based on these figures, the cost impact of
the proposed inspection is estimated to be $260 per airplane.
The cost impact figures discussed above are 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 2003-NM-173-AD.
Applicability: Model 747-400, -400D, and -400F series airplanes;
as listed in Boeing Alert Service Bulletin 747-27A2397, dated July
24, 2003; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct cracking in the yaw damper actuator
portion of the upper and lower rudder power control modules (PCM),
which could result in an uncommanded left rudder hardover,
consequent increased pilot workload, and possible runway departure
upon landing, accomplish the following:
Review of Airplane Maintenance Records
(a) Within 3 months after the effective date of this AD: Review
the airplane maintenance records to determine if each PCM has a main
manifold with less than 15,000 total flight hours or fewer than
2,000 total flight cycles, or do the inspection required by
paragraph (c) of this AD.
Follow-On Actions: PCMs With Less Than 15,000 Total Flight Hours or
Less Than 2,000 Flight Cycles
(b) If it can be positively determined from the review of the
airplane maintenance records that each rudder PCM is below either of
the thresholds specified in paragraph (a) of this AD: Submit a
report to the manufacturer in accordance with paragraph (d) of this
AD.
Follow-On Actions: PCMs With 15,000 Total Flight Hours or More and
2,000 Flight Cycles or More
(c) If it cannot be positively determined that each rudder PCM
is below either of the thresholds specified in paragraph (a) of this
AD: Within 3 months after the effective date of this AD, do an
ultrasonic inspection of the yaw damper actuator portion of the
upper
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and lower rudder PCMs in accordance with the Accomplishment
Instructions specified in Boeing Alert Service Bulletin 747-27A2397,
dated July 24, 2003. After completing the actions required by
paragraphs (c)(1) or (c)(2) of this AD, as applicable, submit a
report to the manufacturer in accordance with paragraph (d) of this
AD.
(1) If no cracking is found: Apply sealant and a torque stripe
and install a lockwire on the applicable rudder PCM per Figure 1 or
Figure 2, as applicable, and the Accomplishment Instructions
specified in Boeing Alert Service Bulletin 747-27A2397, dated July
24, 2003.
(2) If any cracking is found: Before further flight, replace the
affected PCM with a PCM having less than 15,000 total flight hours
and less than 2,000 total flight cycles, or a PCM that has been
ultrasonically inspected (either by the operator or the supplier) in
accordance with the Accomplishment Instructions specified in Boeing
Alert Service Bulletin 747-27A2397, dated July 24, 2003.
Reporting Requirements
(d) At the applicable time specified in paragraph (d)(1) or
(d)(2) of this AD, accomplish paragraph (e).
(1) If the inspection was done after the effective date of this
AD: Submit the report and PCM, if applicable, within 20 days after
the inspection.
(2) If the inspection was accomplished prior to the effective
date of this AD: Submit the report and PCM, if applicable, within 20
days after the effective date of this AD.
(e) Do the requirements of paragraphs (e)(1) and (e)(2) of this
AD. 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) Submit a report of the airplane maintenance records review
or the inspection findings (positive and negative) to: The Boeing
Company, Service Engineering--Mechanical Systems, Attn: R. Adams,
fax: (425) 342-5224. The report must contain the airplane and rudder
PCM serial numbers, the total flight hours and flight cycles for
each rudder PCM, and a description of any damage found. Submission
of the Inspection Report Form (Figure 3 of Boeing Alert Service
Bulletin 747-27A2397, dated July 24, 2003) is an acceptable method
of complying with this requirement.
(2) Send parts to Parker Hannifin Corporation in accordance with
the shipping instructions specified in Appendix A of the service
bulletin.
Parts Installation
(f) As of the effective date of this AD, no person shall install
on any airplane a rudder PCM with 15,000 total flight hours or more,
or 2,000 total flight cycles or more, unless it has been
ultrasonically inspected (either by the operator or the supplier) in
accordance with the Accomplishment Instructions specified in Boeing
Alert Service Bulletin 747-27A2397, dated July 24, 2003.
Alternative Methods of Compliance
(g) In accordance with 14 CFR 39.19, the Manager, Seattle
Aircraft Certification Office, FAA, is authorized to approve
alternative methods of compliance for this AD.
Issued in Renton, Washington, on August 22, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-22001 Filed 8-27-03; 8:45 am]
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