Airworthiness Directives; Boeing Model 747 Airplanes, 58623-58626 [05-20268]
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Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules
accordance with Boeing Alert Service
Bulletin 767–27A0194 or 767–27A0195, both
dated August 21, 2003, as applicable: Within
4,000 flight hours or 24 months after the
effective date of this AD, whichever is first,
accomplish the inspections and perform any
applicable corrective action before further
flight in accordance with Work Package 3 of
the Accomplishment Instructions of Boeing
Service Bulletin 767–27A0194 or Boeing
Service Bulletin 767–27A0195, both Revision
1, both dated July 21, 2005; as applicable.
(h) For Model 767 airplanes that have line
numbers 002 through 175 inclusive:
Accomplishing the initial inspection,
applicable corrective action, and lubrication
before the effective date of this AD in
accordance with Boeing Alert Service
Bulletin 767–27A0185, dated July 10, 2003;
is considered acceptable for compliance with
the applicable actions required by paragraph
(f) of this AD.
Note 1: Boeing Service Bulletins 767–
27A0194 and 767–27A0195, both Revision 1,
both dated July 21, 2005, refer to the 767
Airplane Maintenance Manuals (AMM) in
Table 1 of this AD as additional sources of
service information for accomplishing the
detailed inspections, lubrications, freeplay
measurements, and corrective action.
TABLE 1.—ADDITIONAL SOURCES OF
SERVICE INFORMATION
Boeing AMM
Subject
767–200 ................................
767–200 ................................
27–41–10
12–21–05
Parts Installation
(i) As of the effective date of this AD, no
person may install on any airplane a
horizontal stabilizer trim actuator unless it is
new or has been overhauled in accordance
with Boeing Service Bulletins 767–27A0194
and 767–27A0195, both Revision 1, both
dated July 21, 2005; or has been inspected,
lubricated, and measured in accordance with
paragraph (f) of this AD.
Alternative Methods of Compliance
(AMOCs)
(j) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
Issued in Renton, Washington, on
September 30, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Airplane Certification Service.
[FR Doc. 05–20267 Filed 10–6–05; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22624; Directorate
Identifier 2004–NM–81–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Boeing Model 747 airplanes. This
proposed AD would require the
following actions for the drive
mechanism of the horizontal stabilizer:
Repetitive detailed inspections for
discrepancies and loose ball bearings;
repetitive lubrication of the ballnut and
ballscrew; repetitive measurements of
the freeplay between the ballnut and the
ballscrew; and corrective action if
necessary. This proposed AD is
prompted by a report of extensive
corrosion of a ballscrew in the drive
mechanism of the horizontal stabilizer
on a similar airplane model. We are
proposing this AD to prevent an
undetected failure of the primary load
path for the ballscrew in the horizontal
stabilizer and subsequent wear and
failure of the secondary load path,
which could lead to loss of control of
the horizontal stabilizer and consequent
loss of control of the airplane.
DATES: We must receive comments on
this proposed AD by November 21,
2005.
Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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.
You can get the service information
identified in this proposed AD from
ADDRESSES:
PO 00000
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Sfmt 4702
58623
Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124–2207.
You can examine the contents of this
AD docket on the Internet at https://
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:
Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Airplane
Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98055–4056;
telephone (425) 917–6490; fax (425)
917–6590.
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–2005–99999.’’ The Transport
Airplane Directorate identifier is in the
form ‘‘Directorate Identifier 2005–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–
2005–22624; Directorate Identifier
2004–NM–81–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 https://
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
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Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
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
https://www.faa.gov/language and https://
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 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 DMS
receives them.
Discussion
On January 31, 2000, there was an
accident involving a McDonnell Douglas
Model DC–9–83 (MD–83) airplane. The
National Transportation Safety Board
(NTSB) determined that the probable
cause of this accident was a loss of
airplane pitch control resulting from the
in-flight failure of the acme nut threads
of the jackscrew assembly of the
horizontal stabilizer trim system. The
NTSB concluded that the thread failure
was caused by excessive wear, resulting
from insufficient lubrication of the
jackscrew assembly.
The drive mechanism of the
horizontal stabilizer on McDonnell
Douglas Model DC–9–83 (MD–83)
airplanes has a jackscrew assembly with
an acme screw. The drive mechanism of
the horizontal stabilizer on Boeing
Model 747 airplanes uses a ballscrew.
Acme screws and ballscrews have some
differences in design, but perform
similar functions and have the same
airplane level effect following failure.
The manufacturer’s safety analysis of
the 747 drive mechanism found no
safety problems with the configuration
of the drive mechanism, but showed
that changes to the maintenance
procedures and maintenance intervals
are required to keep the drive
mechanism properly maintained and
operating as designed.
We have received a report indicating
that the ballscrew in the drive
mechanism of the horizontal stabilizer
on a Boeing Model 757 series airplane
showed extensive corrosion, which
could lead to excessive wear. The
ballscrew on Boeing Model 757
airplanes is similar to that on the Boeing
Model 747 airplanes that are the subject
of this proposed AD. Therefore, both of
these airplane models could have the
same unsafe condition. We are
considering separate action for Boeing
Model 757 airplanes and other similar
Boeing airplanes.
Extensive corrosion of the ballscrew
in the drive mechanism of the
horizontal stabilizer, if not corrected,
could cause an undetected failure of the
primary load path for the ballscrew and
subsequent wear and failure of the
secondary load path, which could lead
to loss of control of the horizontal
stabilizer and consequent loss of control
of the airplane.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 747–27A2396, Revision
1, dated August 4, 2005.
The compliance times specified in the
service bulletin is as follows:
For all airplanes: The compliance
times for the initial detailed inspections
and lubrication of the ballnut and
ballscrew is 15,000 total flight hours or
18 months after the original issue date
on the service bulletin, whichever
occurs later. The inspection is repeated
at intervals not to exceed between 2,000
and 4,000 flight hours or 24 months,
whichever occurs first; the lubrication is
repeated at intervals not to exceed 2,000
flight hours or 12 months, whichever
occurs first.
For all airplanes except those on
which an FAA-approved low utilization
maintenance program is in effect: The
compliance time for the initial
ballscrew-to-ballnut freeplay inspection
is 15,000 flight hours after
accomplishing the last ballscrew-toballnut freeplay inspection or 18
months after the original issue date on
the service bulletin, whichever occurs
later. If the inspection has never been
done, the compliance time for the initial
inspection is 15,000 flight hours after
the delivery date of the airplane or 18
months after the original issue date on
the service bulletin, whichever occurs
later. The inspection is repeated at
intervals not to exceed between 18,000
flight hours and 21,000 flight hours.
For all airplanes except those on
which an FAA-approved low utilization
maintenance program is in effect: The
compliance time for the initial
ballscrew-to-ballnut freeplay inspection
is 60 months after accomplishing the
last ballscrew-to-ballnut freeplay
inspection. If the inspection has never
been done, the compliance time for the
initial inspection is within 60 months
after the delivery date of the airplane.
The inspection is repeated at intervals
not to exceed 72 months.
The service bulletin also describes the
procedures in the following table for the
drive mechanism of the horizontal
stabilizer.
PROCEDURES SPECIFIED IN BOEING ALERT SERVICE BULLETIN 747–27A2396
Work package
Repetitive actions
Corrective action
1 ....................
Accomplishing detailed visual inspections for discrepancies (including cracks, corrosion, damage, and worn areas); and a
detailed inspection for loose ball bearings of the external
areas of the drive mechanism and areas below the drive
mechanism.
Lubricating the ballnut and ballscrew of the horizontal stabilizer
drive mechanism.
Measuring the freeplay between the ballnut and ballscrew .......
Replacing the ballscrew actuator with a new or overhaulted actuator if any discrepancy is found during any inspection.
2 ....................
3 ....................
We have determined that
accomplishing the actions specified in
the service bulletin will adequately
address the unsafe condition.
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Not applicable.
Replacing the ballscrew actuator with a new or overhauled actuator if the freeplay is more than the specified limit.
The service bulletin refers to the 747
Airplane Maintenance Manuals (AMM)
in the following table as additional
sources of service information for
accomplishing the detailed inspections,
PO 00000
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lubrications, freeplay measurements,
and corrective action.
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Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules
ADDITIONAL SOURCES OF SERVICE
INFORMATION
Boeing AMM
747–100/200/300 AMM ........
747–100/200/300 AMM ........
747–400 AMM ......................
747–400 AMM ......................
Subject
12–21–19
27–41–06
12–21–19
27–41–06
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
the following actions for the drive
mechanism of the horizontal stabilizer:
• Repetitive detailed inspections for
discrepancies of the ballscrew assembly;
• Repetitive lubrication of the ballnut
and ballscrew;
• Repetitive measurements of
freeplay between the ballnut and the
ballscrew; and
• Corrective action if necessary.
The proposed AD would require you
to use the service bulletin described
previously to perform these actions;
except as discussed under ‘‘Difference
Between the Proposed AD and Service
Information.’’
Differences Between the Proposed AD
and Service Information
The service bulletin specifies
compliance times relative to the date of
issuance of the service bulletin;
however, this proposed AD would
require compliance before the specified
compliance time after the effective date
of this AD.
Costs of Compliance
This proposed AD would affect about
1,082 Model 747 series airplanes
worldwide. The following table
provides the estimated costs for U.S.
operators to comply with this proposed
AD, per cycle.
ESTIMATED COSTS
Repetitive actions
Detailed inspection ............................
Lubrication .........................................
Freeplay measurement ......................
1
1
3
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 will not have federalism
implications under Executive Order
13132. This proposed AD will 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;
VerDate Aug<31>2005
15:27 Oct 06, 2005
Average labor
rate per hour
Work hours
Jkt 208001
$65
65
65
Parts
None ....................
None ....................
None ....................
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, Airplane, 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2005–22624;
Directorate Identifier 2004–NM–81–AD.
PO 00000
Frm 00006
Fmt 4702
Cost per
airplane
Sfmt 4702
$65
65
195
Number of
U.S.-registered
airplanes
236
236
236
Fleet cost
$15,340
15,340
46,020
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this AD
action by November 21, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model
747–100, 747–100B, 747–100B SUD, –200B,
747–200C, 747–200F, 747–300, 747–400,
747–400D, 747–400F, 747SR, and 747SP
series airplanes; certificated in any category.
Unsafe Condition
(d) This AD was prompted by a report of
extensive corrosion of a ballscrew in the
horizontal stabilizer of a similar airplane
model. We are issuing this AD to prevent an
undetected failure of the primary load path
for the ballscrew in the drive mechanism of
the horizontal stabilizer and subsequent wear
and failure of the secondary load path, which
could lead to loss of control of the horizontal
stabilizer and consequent loss of control of
the airplane.
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.
Repetitive Detailed Inspection/Lubrication/
Freeplay Measurement and Corrective
Action
(f) Do all the applicable actions, including
any applicable corrective action, specified in
Work Packages 1, 2, and 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–27A2396, Revision 1,
dated August 4, 2005. Do the actions at the
applicable compliance time specified in
Table 1 of paragraph 1.E. ‘‘Compliance’’ of
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the service bulletin; except, where the service
bulletin specifies a compliance time relative
to the original issue date of the service
bulletin, this AD requires compliance relative
to the effective date of this AD. Where the
service bulletin specifies a compliance time
relative to the delivery date of the airplane,
this AD requires compliance relative to the
date of issuance of the original standard
airworthiness certificate. Do any applicable
corrective action before further flight. Repeat
the actions at the applicable repeat interval
specified in Table 1 of paragraph 1.E
‘‘Compliance’’ of the service bulletin.
Note 1: Boeing Alert Service Bulletin 747–
27A2396, Revision 1, dated August 4, 2005,
refers to the Airplane Maintenance Manuals
(AMMs) in Table 1 of this AD as additional
sources of service information for
accomplishing the detailed visual
inspections, lubrications, freeplay
measurements, and corrective actions.
TABLE 1.—ADDITIONAL SOURCES OF
SERVICE INFORMATION
747–100/200/300 AMM ........
747–100/200/300 AMM ........
747–400 AMM ......................
747–400 AMM ......................
27–41–06
12–21–19
27–41–06
Previously Accomplished Actions
(g) For airplanes on which the drive
mechanism of the horizontal stabilizer was
replaced before the effective date of this AD
with a drive mechanism that was not new or
overhauled, and the detailed and freeplay
inspections were not accomplished in
accordance with Boeing Alert Service
Bulletin 747–27A2396, dated September 4,
2003: Within 4,000 flight hours or 24 months
after the effective date of this AD, whichever
is first, accomplish the inspections, and
perform any applicable corrective action
before further flight, in accordance with
Work Package 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–27A2396, Revision 1, dated August 4,
2005.
Parts Installation
(h) As of the effective date of this AD, no
person may install on any airplane a
horizontal stabilizer trim actuator unless it is
new or has been overhauled in accordance
with Boeing Alert Service Bulletin 747–
27A2396, Revision 1, dated August 4, 2005;
or has been inspected, lubricated, and
measured in accordance with paragraph (f) of
this AD.
Alternative Methods of Compliance
(AMOCs)
(i) The Manager, Seattle Airplane
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
15:27 Oct 06, 2005
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22631; Directorate
Identifier 2005–NM–183–AD]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–120, –120ER,
–120FC, –120QC, and –120RT
Airplanes
Federal Aviation
Administration (FAA), Department of
Subject
Transportation (DOT).
ACTION: Notice of proposed rulemaking
12–21–19
(NPRM).
Boeing AMM
VerDate Aug<31>2005
Issued in Renton, Washington, on
September 30, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Airplane Certification Service.
[FR Doc. 05–20268 Filed 10–6–05; 8:45 am]
Jkt 208001
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Empresa Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–120, –120ER,
–120FC, –120QC, and –120RT airplanes.
This proposed AD would require
modifying electrical harnesses located at
the left- and right-hand wing roots; and
re-routing and modifying the harness of
the right-hand outboard flap actuator.
This proposed AD results from fuel
system reviews conducted by the
manufacturer. We are proposing this AD
to prevent chafed electrical harnesses,
which could result in a potential source
of ignition for fuel vapors near a fuel
tank and consequent fire or fuel tank
explosion.
We must receive comments on
this proposed AD by November 7, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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,
DATES:
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Empresa Brasileira de
Aeronautica S.A. (EMBRAER), P.O. Box
343—CEP 12.225, Sao Jose dos
Campos—SP, Brazil, for service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2474;
fax (425) 227–1149.
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 in the
ADDRESSES section. Include the docket
number ‘‘FAA–2005–22631; Directorate
Identifier 2005–NM–183–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 https://
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 the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://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 receives them.
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]]>Agencies
[Federal Register Volume 70, Number 194 (Friday, October 7, 2005)]
[Proposed Rules]
[Pages 58623-58626]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-20268]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22624; Directorate Identifier 2004-NM-81-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Boeing Model 747 airplanes. This proposed AD would require the
following actions for the drive mechanism of the horizontal stabilizer:
Repetitive detailed inspections for discrepancies and loose ball
bearings; repetitive lubrication of the ballnut and ballscrew;
repetitive measurements of the freeplay between the ballnut and the
ballscrew; and corrective action if necessary. This proposed AD is
prompted by a report of extensive corrosion of a ballscrew in the drive
mechanism of the horizontal stabilizer on a similar airplane model. We
are proposing this AD to prevent an undetected failure of the primary
load path for the ballscrew in the horizontal stabilizer and subsequent
wear and failure of the secondary load path, which could lead to loss
of control of the horizontal stabilizer and consequent loss of control
of the airplane.
DATES: We must receive comments on this proposed AD by November 21,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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.
You can get the service information identified in this proposed AD
from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207.
You can examine the contents of this AD docket on the Internet at
https://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: Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Airplane
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6490; fax (425) 917-6590.
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-2005-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2005-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-2005-22624;
Directorate Identifier 2004-NM-81-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 https://
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
[[Page 58624]]
published on April 11, 2000 (65 FR 19477-78), or you may visit https://
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 https://www.faa.gov/language and https://
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 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 DMS
receives them.
Discussion
On January 31, 2000, there was an accident involving a McDonnell
Douglas Model DC-9-83 (MD-83) airplane. The National Transportation
Safety Board (NTSB) determined that the probable cause of this accident
was a loss of airplane pitch control resulting from the in-flight
failure of the acme nut threads of the jackscrew assembly of the
horizontal stabilizer trim system. The NTSB concluded that the thread
failure was caused by excessive wear, resulting from insufficient
lubrication of the jackscrew assembly.
The drive mechanism of the horizontal stabilizer on McDonnell
Douglas Model DC-9-83 (MD-83) airplanes has a jackscrew assembly with
an acme screw. The drive mechanism of the horizontal stabilizer on
Boeing Model 747 airplanes uses a ballscrew. Acme screws and ballscrews
have some differences in design, but perform similar functions and have
the same airplane level effect following failure. The manufacturer's
safety analysis of the 747 drive mechanism found no safety problems
with the configuration of the drive mechanism, but showed that changes
to the maintenance procedures and maintenance intervals are required to
keep the drive mechanism properly maintained and operating as designed.
We have received a report indicating that the ballscrew in the
drive mechanism of the horizontal stabilizer on a Boeing Model 757
series airplane showed extensive corrosion, which could lead to
excessive wear. The ballscrew on Boeing Model 757 airplanes is similar
to that on the Boeing Model 747 airplanes that are the subject of this
proposed AD. Therefore, both of these airplane models could have the
same unsafe condition. We are considering separate action for Boeing
Model 757 airplanes and other similar Boeing airplanes.
Extensive corrosion of the ballscrew in the drive mechanism of the
horizontal stabilizer, if not corrected, could cause an undetected
failure of the primary load path for the ballscrew and subsequent wear
and failure of the secondary load path, which could lead to loss of
control of the horizontal stabilizer and consequent loss of control of
the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-27A2396,
Revision 1, dated August 4, 2005.
The compliance times specified in the service bulletin is as
follows:
For all airplanes: The compliance times for the initial detailed
inspections and lubrication of the ballnut and ballscrew is 15,000
total flight hours or 18 months after the original issue date on the
service bulletin, whichever occurs later. The inspection is repeated at
intervals not to exceed between 2,000 and 4,000 flight hours or 24
months, whichever occurs first; the lubrication is repeated at
intervals not to exceed 2,000 flight hours or 12 months, whichever
occurs first.
For all airplanes except those on which an FAA-approved low
utilization maintenance program is in effect: The compliance time for
the initial ballscrew-to-ballnut freeplay inspection is 15,000 flight
hours after accomplishing the last ballscrew-to-ballnut freeplay
inspection or 18 months after the original issue date on the service
bulletin, whichever occurs later. If the inspection has never been
done, the compliance time for the initial inspection is 15,000 flight
hours after the delivery date of the airplane or 18 months after the
original issue date on the service bulletin, whichever occurs later.
The inspection is repeated at intervals not to exceed between 18,000
flight hours and 21,000 flight hours.
For all airplanes except those on which an FAA-approved low
utilization maintenance program is in effect: The compliance time for
the initial ballscrew-to-ballnut freeplay inspection is 60 months after
accomplishing the last ballscrew-to-ballnut freeplay inspection. If the
inspection has never been done, the compliance time for the initial
inspection is within 60 months after the delivery date of the airplane.
The inspection is repeated at intervals not to exceed 72 months.
The service bulletin also describes the procedures in the following
table for the drive mechanism of the horizontal stabilizer.
Procedures Specified in Boeing Alert Service Bulletin 747-27A2396
------------------------------------------------------------------------
Work package Repetitive actions Corrective action
------------------------------------------------------------------------
1................... Accomplishing detailed Replacing the ballscrew
visual inspections for actuator with a new or
discrepancies overhaulted actuator if
(including cracks, any discrepancy is
corrosion, damage, and found during any
worn areas); and a inspection.
detailed inspection for
loose ball bearings of
the external areas of
the drive mechanism and
areas below the drive
mechanism.
2................... Lubricating the ballnut Not applicable.
and ballscrew of the
horizontal stabilizer
drive mechanism.
3................... Measuring the freeplay Replacing the ballscrew
between the ballnut and actuator with a new or
ballscrew. overhauled actuator if
the freeplay is more
than the specified
limit.
------------------------------------------------------------------------
We have determined that accomplishing the actions specified in the
service bulletin will adequately address the unsafe condition.
The service bulletin refers to the 747 Airplane Maintenance Manuals
(AMM) in the following table as additional sources of service
information for accomplishing the detailed inspections, lubrications,
freeplay measurements, and corrective action.
[[Page 58625]]
Additional Sources of Service Information
------------------------------------------------------------------------
Boeing AMM Subject
------------------------------------------------------------------------
747-100/200/300 AMM..................................... 12-21-19
747-100/200/300 AMM..................................... 27-41-06
747-400 AMM............................................. 12-21-19
747-400 AMM............................................. 27-41-06
------------------------------------------------------------------------
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 the following actions for the drive mechanism of the
horizontal stabilizer:
Repetitive detailed inspections for discrepancies of the
ballscrew assembly;
Repetitive lubrication of the ballnut and ballscrew;
Repetitive measurements of freeplay between the ballnut
and the ballscrew; and
Corrective action if necessary.
The proposed AD would require you to use the service bulletin
described previously to perform these actions; except as discussed
under ``Difference Between the Proposed AD and Service Information.''
Differences Between the Proposed AD and Service Information
The service bulletin specifies compliance times relative to the
date of issuance of the service bulletin; however, this proposed AD
would require compliance before the specified compliance time after the
effective date of this AD.
Costs of Compliance
This proposed AD would affect about 1,082 Model 747 series
airplanes worldwide. The following table provides the estimated costs
for U.S. operators to comply with this proposed AD, per cycle.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Repetitive actions Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed inspection....................... 1 $65 None........................ $65 236 $15,340
Lubrication............................... 1 65 None........................ 65 236 15,340
Freeplay measurement...................... 3 65 None........................ 195 236 46,020
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 will not have federalism
implications under Executive Order 13132. This proposed AD will 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, Airplane, 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-2005-22624; Directorate Identifier 2004-NM-
81-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by November 21, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model 747-100, 747-100B, 747-
100B SUD, -200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, 747SR, and 747SP series airplanes; certificated in any
category.
Unsafe Condition
(d) This AD was prompted by a report of extensive corrosion of a
ballscrew in the horizontal stabilizer of a similar airplane model.
We are issuing this AD to prevent an undetected failure of the
primary load path for the ballscrew in the drive mechanism of the
horizontal stabilizer and subsequent wear and failure of the
secondary load path, which could lead to loss of control of the
horizontal stabilizer and consequent loss of control of the
airplane.
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.
Repetitive Detailed Inspection/Lubrication/Freeplay Measurement and
Corrective Action
(f) Do all the applicable actions, including any applicable
corrective action, specified in Work Packages 1, 2, and 3 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
27A2396, Revision 1, dated August 4, 2005. Do the actions at the
applicable compliance time specified in Table 1 of paragraph 1.E.
``Compliance'' of
[[Page 58626]]
the service bulletin; except, where the service bulletin specifies a
compliance time relative to the original issue date of the service
bulletin, this AD requires compliance relative to the effective date
of this AD. Where the service bulletin specifies a compliance time
relative to the delivery date of the airplane, this AD requires
compliance relative to the date of issuance of the original standard
airworthiness certificate. Do any applicable corrective action
before further flight. Repeat the actions at the applicable repeat
interval specified in Table 1 of paragraph 1.E ``Compliance'' of the
service bulletin.
Note 1: Boeing Alert Service Bulletin 747-27A2396, Revision 1,
dated August 4, 2005, refers to the Airplane Maintenance Manuals
(AMMs) in Table 1 of this AD as additional sources of service
information for accomplishing the detailed visual inspections,
lubrications, freeplay measurements, and corrective actions.
Table 1.--Additional Sources of Service Information
------------------------------------------------------------------------
Boeing AMM Subject
------------------------------------------------------------------------
747-100/200/300 AMM..................................... 12-21-19
747-100/200/300 AMM..................................... 27-41-06
747-400 AMM............................................. 12-21-19
747-400 AMM............................................. 27-41-06
------------------------------------------------------------------------
Previously Accomplished Actions
(g) For airplanes on which the drive mechanism of the horizontal
stabilizer was replaced before the effective date of this AD with a
drive mechanism that was not new or overhauled, and the detailed and
freeplay inspections were not accomplished in accordance with Boeing
Alert Service Bulletin 747-27A2396, dated September 4, 2003: Within
4,000 flight hours or 24 months after the effective date of this AD,
whichever is first, accomplish the inspections, and perform any
applicable corrective action before further flight, in accordance
with Work Package 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-27A2396, Revision 1, dated August 4,
2005.
Parts Installation
(h) As of the effective date of this AD, no person may install
on any airplane a horizontal stabilizer trim actuator unless it is
new or has been overhauled in accordance with Boeing Alert Service
Bulletin 747-27A2396, Revision 1, dated August 4, 2005; or has been
inspected, lubricated, and measured in accordance with paragraph (f)
of this AD.
Alternative Methods of Compliance (AMOCs)
(i) The Manager, Seattle Airplane Certification Office (ACO),
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 September 30, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Airplane Certification
Service.
[FR Doc. 05-20268 Filed 10-6-05; 8:45 am]
BILLING CODE 4910-13-P
