[Federal Register: September 7, 2004 (Volume 69, Number 172)]
[Proposed Rules]
[Page 54060-54063]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07se04-18]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18999; Directorate Identifier 2003-NM-259-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400, -400D, and -400F
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 747-400, -400D, and -400F series airplanes.
This proposed AD would require replacing at least one flap control unit
(FCU) in the main equipment center with a new or modified FCU. This
proposed AD is prompted by a report indicating that, after takeoff, an
airplane was required to return to the airport because the autopilot
disengaged. The report also indicated that, upon selecting flaps for
landing, the flaps indication display did not indicate the flap
setting, requiring the airplane to land in alternate flap mode. We are
proposing this AD to prevent disconnection of autoland/autopilot
functions and loss of primary flaps control and flaps indication
display due to disengagement of all three FCUs at the same time, which
could lead to a non-normal high speed landing with the flaps retracted,
increased pilot workload, and possible runway departure at high speeds
during landing.
DATES: We must receive comments on this proposed AD by October 22,
2004.
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.
By 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.
[[Page 54061]]
For the service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401 on
the plaza level of the Nassif Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Technical Information: 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.
Plain Language Information: Marcia Walters, marcia.walters@faa.gov.
SUPPLEMENTARY INFORMATION:
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-18999;
Directorate Identifier 2003-NM-259-AD'' in the subject line 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 submitted 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
that 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 may review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications that affect you. You can get more information about
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.Examining
the Docket
You can examine the AD docket 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 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 DMS receives them.
Discussion
We have received a report indicating that, after takeoff, a Boeing
Model 747-400 series airplane was required to return to the airport
because the autopilot disengaged. The report also indicated that, upon
selecting flaps for landing, the flaps indication display did not
indicate the flap setting, requiring the airplane to land in alternate
flap mode. The root cause of these conditions has been determined to be
the susceptibility of the flap control units (FCUs) to certain external
failures of the position switch circuit of the leading edge flap. These
external failures can cause all three FCUs to disengage at the same
time, which could result in disconnection of autoland/autopilot
functions and loss of primary flaps control and flaps indication
display. These conditions, if not corrected, could lead to a non-normal
high speed landing with the flaps retracted, increased pilot workload,
and possible runway departure at high speeds during landing.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-27A2386, dated
March 13, 2003, which describes procedures for replacing FCUs having
part number (P/N) 285U0011-207, located in the main equipment center,
with new or modified FCUs having P/N 285U0011-208. The service bulletin
specifies that at least one FCU per airplane must be replaced to
prevent the malfunction of the primary flaps control and flaps
indication display.
Boeing Alert Service Bulletin 747-27A2386 refers to Boeing
Component Service Bulletin 285U0011-27-06, dated March 13, 2003, as an
additional source of service information for modifying an FCU having P/
N 285U0011-207 to P/N 285U0011-208.
Boeing Alert Service Bulletin 747-27A2386 also specifies prior or
concurrent accomplishment of Boeing Service Bulletin 747-27-2319, dated
January 24, 1991, which describes procedures for replacing FCUs having
P/N 285U0011-205 or 285U0011-206, located in the main equipment center,
with new or modified FCUs having P/N 285U0011-207.
Boeing Service Bulletin 747-27-2319 refers to Boeing Component
Service Bulletin 285U0011-27-04, dated January 24, 1991, as an
additional source of service information for modifying an FCU having P/
N 285U0011-205 or 285U0011-206 to P/N 285U0011-207.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
Clarification of FCU Replacement Specified in Boeing Alert Service
Bulletin
Although the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-27A2386 specify to ``replace the FCUs as shown in Figure
1'' (which illustrates replacement of three FCUs), only a minimum of
one FCU for each airplane must be replaced as specified in paragraph
1.E., ``Compliance,'' of the service bulletin. In paragraph 1.D.,
``Description,'' the service bulletin specifies that ``a minimum of one
FCU for each airplane must be replaced to prevent the malfunction of
the primary flaps control and flaps indication display.'' Replacing a
minimum of one FCU having P/N 285U0011-207 with P/N 285U0011-208
addresses the unsafe condition specified in the proposed AD.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. Therefore, we are proposing this AD, which
would require replacing at least one FCU having P/N 285U0011-207,
located in the main equipment center, with an FCU having P/N 285U0011-
208. For certain
[[Page 54062]]
airplanes, the proposed AD would first require replacing the three FCUs
having P/N 285U0011-205 or 285U0011-206 with FCUs having P/N 285U0011-
207. The proposed AD would require you to use Boeing Alert Service
Bulletin 747-27A2386, dated March 13, 2003; and Boeing Service Bulletin
747-27-2319, dated January 24, 1991; described previously to perform
these actions.
Costs of Compliance
This proposed AD would affect about 614 airplanes worldwide and 87
airplanes of U.S. registry. The following table provides the estimated
costs for U.S. operators to comply with this proposed AD.
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Average
Replacement Work hours labor rate Parts Cost per
per hour airplane
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Estimated Costs
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With new -208 FCU........................................... 2 $65 $78,550 $78,680
With modified -208 FCU...................................... 10 65 975 1,625
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Estimated Concurrent Service Bulletin Costs
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With new -207 FCU........................................... 3 65 235,650 235,845
With modified -207 FCU...................................... 87 65 2,925 8,580
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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 adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA-2004-18999; Directorate Identifier 2003-NM-
259-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive comments
on this AD action by October 22, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 747-400, -400D, and -400F series
airplanes, as listed in Boeing Alert Service Bulletin 747-27A2386,
dated March 13, 2003; certificated in any category.
Unsafe Condition
(d) This AD was prompted by a report indicating that, after
takeoff, an airplane was required to return to the airport because the
autopilot disengaged. The report also indicated that, upon selecting
flaps for landing, the flaps indication display did not indicate the
flap setting, requiring the airplane to land in alternate flap mode. We
are issuing this AD to prevent disconnection of autoland/autopilot
functions and loss of primary flaps control and flaps indication
display due to disengagement of all three flap control units (FCUs) at
the same time, which could lead to a non-normal high speed landing with
the flaps retracted, increased pilot workload, and possible runway
departure at high speeds during 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.
Replace FCU
(f) At the earliest of the times specified in paragraphs (f)(1),
(f)(2), and (f)(3) of this AD: Replace at least one FCU having P/N
285U0011-207 with a new or modified FCU having P/N 285U0011-208 in
accordance with the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-27A2386, dated March 13, 2003.
(1) Within 60 months after the effective date of this AD.
(2) Within 25,000 flight hours after the effective date of this AD.
(3) Within 4,000 flight cycles after the effective date of this AD.
Note 1: Boeing Alert Service Bulletin 747-27A2386, dated March
13, 2003, refers to Boeing Component Service Bulletin 285U0011-27-
06, dated March 13, 2003, as an additional source of service
information for modifying an FCU having P/N 285U0011-207 to P/N
285U0011-208.
Actions Required Before or Concurrently With Paragraph (f)
(g) For airplanes listed in Boeing Service Bulletin 747-27-2319,
dated January 24, 1991: Before or concurrent with the accomplishment
of paragraph (f) of this AD, replace the three FCUs having P/N
285U0011-205 or 285U0011-206 with new or modified FCUs having P/N
285U0011-207 in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-27-2319, dated January 24, 1991.
Note 2: Boeing Service Bulletin 747-27-2319, dated January 24,
1991, refers to Boeing Component Service Bulletin 285U0011-27-04,
dated January 24, 1991, as an additional source of service
information for modifying
[[Page 54063]]
the FCUs having P/N 285U0011-205 or 285U0011-206 to P/N 285U0011-
207.
Parts Installation
(h) As of the effective date of this AD, no person may install
on any airplane an FCU having P/N 285U0011-205 or -206.
Alternative Methods of Compliance (AMOCs)
(i) The Manager, Seattle Aircraft Certification Office, FAA, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Issued in Renton, Washington, on August 25, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-20210 Filed 9-3-04; 8:45 am]
BILLING CODE 4910-13-P