[Federal Register: February 13, 2006 (Volume 71, Number 29)]
[Proposed Rules]
[Page 7446-7449]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13fe06-14]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23873; Directorate Identifier 2005-NM-110-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400, 747-400D, and
747-400F Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Boeing Model 747-400, 747-400D,
and 747-400F series airplanes. The existing AD currently requires
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
all airplane
[[Page 7447]]
maintenance records review and inspection results to the manufacturer.
This proposed AD would expand the applicability and discontinue certain
requirements of the existing AD. This proposed AD would require
repetitive inspections of the PCMs and replacement of the PCMs if
necessary. This proposed AD results from manufacturer findings that the
inspections required by the existing AD must be performed at regular
intervals. We are proposing this AD 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.
DATES: We must receive comments on this proposed AD by March 30, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
FOR FURTHER INFORMATION CONTACT: Douglas 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
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2006-23873;
Directorate Identifier 2005-NM-110-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
(DMS) receives them.
Discussion
On November 3, 2003, we issued AD 2003-23-01, amendment 39-13364
(68 FR 64263, November 13, 2003), for certain Boeing Model 747-400,
747-400D, and 747-400F series airplanes. That AD requires reviewing
airplane maintenance records; inspecting the yaw damper actuator
portion of the upper and lower power control modules (PCM) for
cracking, and replacing the PCMs if necessary; and reporting airplane
maintenance records review and inspection results to the manufacturer.
That AD was prompted by 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. We issued that AD 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.
Actions Since Existing AD Was Issued
The preamble to AD 2003-23-01 explains that we consider the
requirements ``interim action.'' The inspection reports required by
that AD were intended to 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. We
now have determined that further rulemaking is necessary, and this
proposed AD follows from that determination.
Since we issued AD 2003-23-01, there have been no further reports
of a failure of the yaw damper actuator portion of the lower rudder PCM
manifold. Also, investigations that included inspection results
gathered during accomplishment of the original release of Boeing Alert
Service Bulletin 747-27A2397, dated July 24, 2003 (which is referenced
as the appropriate source of service information for doing the actions
required by AD 2003-23-01), did not yield any explanation as to the
cause of the cracks in the yaw damper actuator portion of the lower
rudder PCM manifold. However, the failure that led to the issuance of
AD 2003-23-01 highlighted a previously unidentified single point
failure. Without inspection of the yaw damper actuator portion of the
lower rudder PCM manifold, a developing crack can remain latent and
grow to the point of failure. Therefore, to ensure that no latent crack
can develop undetected to the point of failure of the PCM manifold, it
has been determined that regular repetition of the inspection required
by AD 2003-23-01 is necessary for all Boeing Model 747-400, 747-400D,
and 747-400F series airplanes.
The compliance time for the initial inspection (for airplanes not
previously inspected as required by AD 2003-23-01) has been revised to
the earlier of 56,000 total flight hours or 9,000 total flight cycles,
or, for airplanes that are close to or have exceeded that total, 24
months after the effective date of the AD. This compliance time is
based on the data gathered from airplanes inspected in accordance with
AD 2003-23-01, including the fact that there have been no further
reports of a failure of the yaw damper actuator portion of the lower
rudder PCM manifold. We find that this initial compliance time will be
adequate to ensure the safety of the affected airplane fleet.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-27A2397,
Revision 1, dated March 31, 2005. The service
[[Page 7448]]
bulletin describes procedures for performing repetitive ultrasonic
inspections for cracking of the yaw damper actuator portion of the
upper and lower rudder PCMs; reporting the finding of any indication of
a cracked or broken PCM to the airplane manufacturer; and returning any
cracked or broken part to the PCM manufacturer.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2003-23-01. This proposed AD would expand the
applicability of the existing AD and require accomplishing all actions
specified in Boeing Alert Service Bulletin 747-27A2397, Revision 1,
described previously.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Costs of Compliance
There are approximately 636 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 86 airplanes of U.S. registry
would be affected by this proposed AD, and that it would take
approximately 4 work hours per airplane to accomplish the ultrasonic
inspection, at an average labor rate of $65 per work hour. Based on
these figures, the cost impact of the inspection is estimated to be
$22,360, or $260 per airplane, per inspection cycle.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the 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. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by removing amendment 39-13364 (68 FR
64263, November 13, 2003) and adding the following new airworthiness
directive (AD):
Boeing: Docket No. FAA-2006-23873; Directorate Identifier 2005-NM-
110-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by March 30, 2006.
Affected ADs
(b) This AD supersedes AD 2003-23-01.
Applicability
(c) This AD applies to all Boeing Model 747-400, 747-400D, and
747-400F series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from manufacturer findings that the
inspections required by AD 2003-23-01 must be performed at regular
intervals. We are issuing this AD to detect and correct potential
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.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Verification of Rudder PCM/Main Manifold Time in Service
(f) For any affected airplane, if it can be positively verified
that any rudder PCM or PCM main manifold installed on that airplane
has accumulated a different total of flight hours or flight cycles
than the totals accumulated by that airplane, the flight cycles or
flight hours accumulated by the rudder PCM or PCM main manifold will
be acceptable as valid starting points for meeting the compliance
times required by this AD.
Inspection Accomplished Prior to the Issuance of This AD
(g) For airplanes which, prior to the effective date of this AD,
have received an ultrasonic inspection for cracking of the yaw
damper actuator portion of the upper and lower rudder PCM, in
accordance with Boeing Alert Service Bulletin 747-27A2397, dated
July 24, 2003, as required by AD 2003-23-01, do paragraphs (g)(1),
(g)(2), (g)(3), and (g)(4) of this AD, as applicable, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-27A2397, Revision 1, dated March 31, 2005.
(1) Perform the ultrasonic inspection described in paragraph (g)
of this AD at the later of the times specified in paragraph
(g)(1)(i) or (g)(1)(ii) of this AD, then do paragraph (g)(2) or
(g)(3) of this AD, as applicable; and paragraph (g)(4) of this AD.
(i) Within 28,000 flight hours or 4,500 flight cycles after the
date of the prior inspection, whichever occurs first.
(ii) Within 24 months after the effective date of this AD.
(2) If no cracking is found during any inspection required by
paragraph (g)(1) or (h) of this AD: Apply sealant and a torque
stripe and install a lockwire on the rudder PCM in accordance with
the Accomplishment Instructions and Figure 1 or Figure 2, as
applicable, of Alert Service Bulletin 747-27A2397, Revision 1.
(3) If any cracking is found during any inspection required by
paragraph (g)(1) or (h) of this AD: Before further flight, replace
the affected PCM with a new or serviceable PCM and submit the report
required by paragraph (i) of this AD.
(4) Repeat the ultrasonic inspection described in paragraph (g)
of this AD at intervals not to exceed 28,000 flight hours or 4,500
flight cycles, whichever occurs first,
[[Page 7449]]
and repeat the actions of paragraph (g)(2) or (g)(3) of this AD, as
applicable.
Initial Inspection
(h) For airplanes not inspected prior to the effective date of
this AD as specified in paragraph (g) of this AD: At the later of
the times specified in paragraph (h)(1) or (h)(2) of this AD,
perform an ultrasonic inspection for cracking of the yaw damper
actuator portion of the upper and lower rudder PCM main manifold;
and the actions specified in paragraph (g)(2) or (g)(3) of this AD,
as applicable; in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-27A2397, Revision 1, dated March
31, 2005. Repeat the inspection thereafter at intervals not to
exceed 28,000 flight hours or 4,500 flight cycles, whichever occurs
first.
(1) Prior to the accumulation of 56,000 total flight hours or
9,000 total flight cycles, whichever occurs first.
(2) Within 24 months after the effective date of this AD.
Reporting Requirements and Damaged Parts Disposition
(i) For all airplanes: At the applicable time specified in
paragraph (i)(1) or (i)(2) of this AD, accomplish paragraph (j) of
this AD.
(1) If the inspection was done after the effective date of this
AD: Submit the report and part, if applicable, within 30 days after
the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report and part, if applicable, within 30 days after
the effective date of this AD.
(j) At the applicable time specified in paragraph (i) of this
AD: Do the requirements of paragraphs (j)(1) and (j)(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) If any inspection required by this AD reveals any indication
of a cracked or broken part, submit a report to: The Boeing Company,
Service Engineering--Mechanical Systems. The report must contain the
airplane and rudder PCM serial numbers, the total flight hours and
flight cycles for each rudder PCM (and rudder PCM main manifold, if
known), and a description of any damage found. Submission of the
Inspection Report Form (Figure 3 of Boeing Alert Service Bulletin
747-27A2397, Revision 1, dated March 31, 2005) is one acceptable
method of complying with this requirement.
(2) Send any cracked or broken PCMs to Parker Hannifin
Corporation in accordance with the shipping instructions specified
in Appendix A of Boeing Alert Service Bulletin 747-27A2397, Revision
1.
Prior Accomplishment of Requirements
(k) Actions accomplished before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 747-27A2397, dated
July 24, 2003, shall be considered acceptable for compliance with
the corresponding requirements of this AD.
Parts Installation
(l) As of the effective date of this AD, no person shall install
on any airplane a rudder PCM having part number (P/N) 332700-1003, -
1005, -1007, or -1009; or P/N 333200-1003, -1005, -1007, or -1009;
unless the PCM has been ultrasonically inspected (either by the
operator or the supplier) in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-27A2397, Revision
1, dated March 31, 2005.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously according to AD 2003-23-01,
amendment 39-13364, are approved as AMOCs with this AD.
Issued in Renton, Washington, on January 31, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-1944 Filed 2-10-06; 8:45 am]
BILLING CODE 4910-13-P