[Federal Register: November 15, 2006 (Volume 71, Number 220)]
[Proposed Rules]
[Page 66474-66480]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15no06-17]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26323; Directorate Identifier 2006-NM-150-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Boeing Model 737 airplanes. The
existing AD currently requires installation of a new rudder control
system and changes to the adjacent systems to accommodate that new
rudder control system. For certain airplanes, this proposed AD would
add, among other actions, repetitive tests of the force fight monitor
of the main rudder power control unit (PCU), repetitive tests of the
standby hydraulic actuation system, and corrective action; as
applicable. For those airplanes, this proposed AD also would add, among
other actions, replacement of both input control rods of the main
rudder PCU and the input control rod of the standby rudder PCU with new
input control rods, as applicable, which would end the repetitive
tests. For certain other airplanes, this proposed AD would add
installation of an enhanced rudder control system in accordance with
new service information. This proposed AD results from a report of a
fractured rod end on an input control rod of the main rudder PCU. We
are proposing this AD to prevent failure of one of the two input
control rods of main rudder PCU, which, under certain conditions, could
result in reduced controllability of the airplane; and to prevent
failure of any combination of two input control rods of the main rudder
PCU and/or standby rudder PCU, which could result in loss of control of
the airplane. We are also proposing this AD to prevent an uncommanded
rudder hardover event and consequent loss of control of the airplane
due to inherent failure modes, including single-jam modes, and certain
latent failures or jams combined with a second failure or jam.
DATES: We must receive comments on this proposed AD by January 2, 2007.
[[Page 66475]]
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.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Kenneth W. Frey, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6468; 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 in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2006-26323; Directorate Identifier 2006-NM-150-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
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 may
visit http://dms.dot.gov.
Examining the Docket
You may 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
receives them.
Discussion
On October 30, 2002, we issued AD 2002-20-07 R1, amendment 39-12940
(67 FR 67518, November 6, 2002), for all Boeing Model 737 airplanes.
That AD requires installation of a new rudder control system and
changes to the adjacent systems to accommodate that new rudder control
system. That AD resulted from FAA determinations that the existing
system design architecture is unsafe. We issued that AD to prevent an
uncommanded rudder hardover event and consequent loss of control of the
airplane due to inherent failure modes, including single-jam modes, and
certain latent failures or jams combined with a second failure or jam.
Actions Since Existing AD Was Issued
Since the issuance of AD 2002-20-07 R1, we have received a report
of a fractured rod end on one of the two input control rods of the main
rudder power control unit (PCU) on a Model 737-800 series airplane.
This condition was discovered during heavy maintenance. The rod end had
not separated from the input control rod and was retained by the
sealant used during the assembly of the input control rod. The
condition was discovered because the aft rod end of the lower input
control rod appeared loose. If the rod end does not separate from the
input control rod, there is no indication of fracture and it will not
likely be detected during normal flight operation.
If a rod end separates from an input control rod of the main rudder
PCU, the input to the A and B sides of the main rudder PCU (the main
rudder PCU is a dual tandem actuator) will not match. This condition
will cause a force fight between the A and B sides in the main rudder
PCU, which will activate the force fight monitor, activate the standby
hydraulic system, and illuminate the STBY RUD ON light on the P5-3
panel. Dispatch is not allowed with the STBY RUD ON light illuminated.
The incident airplane had been modified to comply with the
requirements of AD 2002-20-07 R1. We previously approved the service
bulletins in the table titled ``Previously Approved Service Bulletins''
as an alternative method of compliance (AMOC) for the requirements of
AD 2002-20-07 R1. These service bulletins include procedures to replace
both input control rods of the main rudder PCU and the input control
rod of the standby rudder PCU (for certain airplanes) with new input
control rod(s) having part number (P/N) 251A3495-1, which, we have
since determined, had an improper heat treatment during manufacture.
Previously Approved Service Bulletins
------------------------------------------------------------------------
For model-- Boeing Service Bulletin
------------------------------------------------------------------------
737-100, -200, and -200C 737-27-1252, Revision 2, dated December
series airplanes. 9, 2004; Revision 1, dated September 25,
2003; and Original Issue, dated June 26,
2003.
737-300, -400, and -500 737-27-1255, Revision 2, dated July 22,
series airplanes. 2004; Revision 1, dated June 26, 2003;
and Original Issue, dated May 1, 2003.
737-600, -700, -700C, -800, 737-27-1253, Revision 2, dated October 7,
and -900 series airplanes. 2004; Revision 1, dated March 27, 2003;
and Original Issue, dated January 2,
2003.
------------------------------------------------------------------------
Failure of one of the two input control rods of the main rudder PCU
under certain conditions, if not corrected, could result in reduced
controllability of the airplane. Failure of any combination of two
input control rods of the main rudder PCU and/or standby rudder PCU, if
not corrected, could result in loss of control of the airplane.
[[Page 66476]]
Relevant Service Information
We have reviewed the service bulletins in the table titled
``Service Bulletins for Repetitive Tests and Other Actions.'' The
service bulletins specify an initial compliance time for doing the
initial test of the standby system of within 60 days after the date of
the service bulletin, and a repetitive interval of 500 flight hours.
The service bulletins also specify an initial compliance time for doing
the initial test of the force fight monitor of within 90 days or 6,000
flight hours after the date of the service bulletin, depending on the
airplane configuration, and a repetitive interval of 6,000 flight
hours. For airplanes identified as Groups 1 and 2, Configuration 2, in
Boeing Alert Service Bulletin 737-27A1281, dated June 14, 2006; and
airplanes identified as Group 1, Configuration 2, in Boeing Alert
Service Bulletin 737-27A1280, dated May 25, 2006; no work is necessary
in accordance with these service bulletins. The improperly heat-treated
control rods were not installed on those airplanes.
Service Bulletins for Repetitive Tests and Other Actions
------------------------------------------------------------------------
Boeing Alert Describes procedures
For certain model-- Service Bulletin for doing--
------------------------------------------------------------------------
737-600, -700, -700C, -800 and 737-27A1280, The ``Rudder Main
-900 series airplanes. dated May 25, Power Control Unit
2005. Force Fight Monitor
Test,'' the
``Operational Test
of the Standby
Hydraulic Actuation
System,'' and
applicable
corrective action if
necessary.
737-100, -200, -200C, -300, - 737-27A1281, The ``Rudder Main
400, and -500 series dated June 14, Power Control Unit
airplanes. 2006. Force Fight Test,''
the ``Standby Rudder
Actuator Shutoff
Valve Test,'' and
applicable
corrective action if
necessary.
------------------------------------------------------------------------
We also have reviewed the service bulletins in the table titled,
``Service Bulletins for Installation of an RSEP and Replacement of
Input control rods.'' Boeing uses the acronym RSEP for the ``Rudder
System Enhancement Program.''
Service Bulletins for Installation of an RSEP and Replacement of Input Control Rods
----------------------------------------------------------------------------------------------------------------
Which ends the
repetitive tests
For certain model-- Boeing-- Describes procedures for-- specified in Boeing
Service Bulletin--
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737-100, -200, and -200C series Service Bulletin 737- Installing an RSEP (Part 737-27A1281, dated
airplanes. 27-1252, Revision 3, 1), and replacing both June 14, 2006.
dated May 12, 2006. input control rods of the
main rudder PCU with new
input control rods (Part
2).
737-300, -400, and -500 series Service Bulletin 737- Installing an RSEP (Part 737-27A1281, dated
airplanes. 27-1255, Revision 3, 1), and replacing both June 14, 2006.
dated May 10, 2006. input control rods of the
main rudder PCU with new
input control rods (Part
2).
737-600, -700, -700C, -800, and - Service Bulletin 737- Installing an RSEP (Part 737-27A1280, dated May
900 series airplanes. 27-1253, Revision 3, 1); and replacing both 25, 2005.
dated May 12, 2006. input control rods of the
main rudder PCU with new
input control rods,
inspecting the control rod
of the standby rudder PCU
to determine if part
number (P/N) 251A3495-1 is
installed, and doing
corrective action if
necessary (Part 2) (i.e.,
replacing any improperly
heat-treated input control
rod with a new input
control rod).
Alert Service Bulletin Replacing both input 737-27A1280, dated May
737-27A1279, dated control rods of the main 25, 2005.
June 20, 2006. rudder PCU and the input
control rod of the standby
rudder PCU with new input
control rod(s).
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletins 737-27-1252, 737-27-1253, and 737-
27-1255, all Revision 3, also specify prior or concurrent
accomplishment of the actions described in the table titled, ``Prior/
Concurrent Service Information.''
Prior/Concurrent Service Information
----------------------------------------------------------------------------------------------------------------
Prior to or concurrently with the
actions in Boeing Alert Service Do this action-- In accordance with--
Bulletin--
----------------------------------------------------------------------------------------------------------------
737-27-1252, Revision 3, dated May 12, Remove the rudder position Boeing Service Bulletin 737-22-1042,
2006. sensor of the automatic Revision 1, dated April 5, 1985.
flight control system.
Replace the rudder feel and Boeing Service Bulletin 737-27-1026,
centering assembly with a new dated January 15, 1971.
all-mechanical unit.
Install the rudder pressure Boeing Service Bulletin 737-27A1206,
reducer and yaw damper Revision 3, dated December 14, 2000.
coupler.
Install provisional wires for Boeing Service Bulletin 737-27-1246,
rudder system enhancement. Revision 1, dated February 21, 2002.
Replace the P5-3 panel with a Boeing Service Bulletin 737-27-1263,
new panel. Revision 1, dated September 25, 2003.
[[Page 66477]]
Replace the input lever for Smiths Aerospace Service Bulletin 1150-
the auxiliary rudder power 27-05A, dated August 28, 2003.
control package with a new
input lever.
737-27-1253, Revision 3, dated May 12, Install provisional wires for Boeing Service Bulletin 737-27-1247,
2006. rudder system enhancement. Revision 1, dated July 25, 2002.
Replace the P5-3 panel with a Boeing Service Bulletin 737-27-1262,
new panel. dated December 19, 2002.
Relocate the wire bundle Boeing Alert Service Bulletin 737-
routing in the vertical 27A1239, dated January 11, 2001.
stabilizer.
737-27-1255, Revision 3, dated May 10, Install provisional wires for Boeing Service Bulletin 737-27-1246,
2006. rudder system enhancement. Revision 1, dated February 21, 2002.
Replace the P5-3 panel with a Boeing Service Bulletin 737-27-1265,
new panel. Revision 1, dated April 3, 2003.
Install a new yaw damper Boeing Service Bulletin 737-27A1206,
coupler. Revision 3, dated December 14, 2000.
Inspect and rework the Boeing Service Bulletin 737-55-1052,
trailing edge beam on the Revision 1, dated August 5, 2004.
vertical fin.
Replace the input lever for Smiths Aerospace Service Bulletin 1150-
the auxiliary rudder power 27-05A, dated August 28, 2003.
control package with a new
input lever.
----------------------------------------------------------------------------------------------------------------
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
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 2002-20-07 R1 and would retain the requirements of
the existing AD. This proposed AD would also require accomplishing the
actions specified in the applicable service information described
previously. For certain airplanes, this proposed AD also would require
suspending a certain Master Minimum Equipment Item, until the
improperly heat-treated input control rods are replaced.
Change to Existing AD
This proposed AD would retain all requirements of AD 2002-20-07 R1.
Since AD 2002-20-07 R1 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement
Requirement in AD 2002-20-07 R1 in this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (b) (with new
title).
------------------------------------------------------------------------
Costs of Compliance
There are about 6,412 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 1,678 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD. The average labor rate
is $80 per work hour.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Work
Action hours Parts Cost per airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
Installation of rudder control 700 $140,000.......... $196,000..................... $328,888,000.
system (required by AD 2002-20-
07 R1, and retained in this
NPRM).
Repetitive tests, per test 2 None.............. $160, per test cycle......... Up to $268,480
cycle (new action proposed by depending on the
this NPRM). configuration of
the airplanes.
Replacement of the input 5 to 7 The manufacturer $400 to $560................. Up to $939,680,
control rods (new action states that it depending the
proposed by this NPRM) (ends will supply configuration of
repetitive tests). required parts to the airplanes.
the operators at
no cost.
----------------------------------------------------------------------------------------------------------------
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
[[Page 66478]]
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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-12940 (67 FR 67518, November 6, 2002) and adding
the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2006-26323; Directorate Identifier 2006-NM-
150-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by January
2, 2007.
Affected ADs
(b) This AD affects the ADs specified in paragraphs (b)(1),
(b)(2), and (b)(3) of this AD.
(1) This AD supersedes AD 2002-20-07 R1.
(2) For airplanes on which the actions required by paragraph (f)
of this AD have been done before the effective date of this AD:
Doing the actions in paragraph (f) of this AD ends the requirements
of the ADs listed in Table 1 of this AD.
(3) For airplanes on which the actions required by paragraph (f)
of this AD have not been done before the effective date of this AD:
Doing the actions in paragraph (h) of this AD ends the requirements
of the ADs listed in Table 1 of this AD.
Table 1.--Other ADs
------------------------------------------------------------------------
AD Amendment
------------------------------------------------------------------------
97-09-15 R1............................................. 39-10912
99-11-05................................................ 39-11175
2000-22-02 R1........................................... 39-11948
------------------------------------------------------------------------
Applicability
(c) This AD applies to all Boeing Model 737-100, -200, -200C, -
300, -400, -500, -600, -700,-700C, -800 and -900 series airplanes,
certificated in any category.
Unsafe Condition
(d) This AD results from a report of a fractured rod end on an
input control rod of the main rudder power control unit (PCU). We
are issuing this AD to prevent failure of one of the two input
control rods of the main rudder PCU, which, under certain
conditions, could result in reduced controllability of the airplane;
and to prevent failure of any combination of two input control rods
of the main rudder PCU and/or standby rudder PCU, which could result
in loss of control of the airplane. We are also issuing this AD to
prevent an uncommanded rudder hardover event and consequent loss of
control of the airplane due to inherent failure modes, including
single-jam modes, and certain latent failures or jams combined with
a second failure or jam.
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.
Requirements of AD 2002-20-07 R1
Installation
(f) Except as provided by paragraphs (h) and (i) of this AD:
Within 6 years after November 12, 2002 (the effective date of AD
2002-20-07), do the actions required by paragraphs (f)(1) and (f)(2)
of this AD, in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA.
(1) Install a new rudder control system that includes new
components such as an aft torque tube, hydraulic actuators, and
associated input control rods, and additional wiring throughout the
airplane to support failure annunciation of the rudder control
system in the flight deck. The system also must incorporate two
separate inputs, each with an override mechanism, to two separate
servo valves on the main rudder PCU; and an input to the standby PCU
that also will include an override mechanism.
(2) Make applicable changes to the adjacent systems to
accommodate the new rudder control system.
New Requirements of This AD
For Certain Airplanes: Tests, Suspension of Certain Master Minimum
Equipment Item, Replacements, Inspection, and Corrective Actions
(g) For airplanes on which the actions required by paragraph (f)
of this AD have been done before the effective date of this AD: Do
the actions in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, as
applicable.
(1) At the applicable times listed in paragraph 1.E.,
``Compliance,'' of the applicable service bulletin specified in
Table 2 of this AD; except, where the service bulletin specifies a
compliance time from the date on the service bulletin, this AD
requires compliance within the specified compliance time after the
effective date of this AD: Do the tests specified in Table 2 of this
AD, until the installation required by paragraph (g)(3) of this AD
has been done in accordance with the applicable service bulletin in
Table 3 of this AD. Do all applicable corrective actions specified
in Table 2 of this AD before further flight.
Table 2.--Repetitive Tests
----------------------------------------------------------------------------------------------------------------
In accordance with the
For model-- Identified as-- Do-- accomplishment instructions
of--
----------------------------------------------------------------------------------------------------------------
(i) 737-100, -200, and -200C Group 1, The ``Rudder Main Power Control Boeing Alert Service Bulletin
series airplanes. Configuration 1 Unit Force Fight Test,'' the 737-27A1281, dated June 14,
in the service ``Standby Rudder Actuator 2006.
bulletin. Shutoff Valve Test,'' and any
applicable corrective action.
(ii) 737-300, -400, and -500 Group 2, The ``Rudder Main Power Control Boeing Alert Service Bulletin
series airplanes. Configuration 1 Unit Force Fight Test,'' the 737-27A1281, dated June 14,
in the service ``Standby Rudder Actuator 2006.
bulletin. Shutoff Valve Test,'' and any
applicable corrective action.
[[Page 66479]]
(iii) 737-600, -700, -700C, - Group 1, The ``Rudder Main Power Control Boeing Alert Service Bulletin
800, and -900 series Configuration 1 Unit Force Fight Monitor 737-27A1280, dated May 25,
airplanes. and Group 2, Test,'' the ``Operational Test 2005.
Configurations of the Standby Hydraulic
1 and 2 in the Actuation System,'' and any
service applicable corrective action.
bulletin.
----------------------------------------------------------------------------------------------------------------
(2) As of the effective date of this AD, do not use the Master
Minimum Equipment Item 27-21, ``STBY RUD ON light,'' until the
actions required by paragraph (g)(3) of this AD are done.
(3) Within 24 months after the effective date of this AD, do the
replacement(s) and inspection, as applicable, specified in Table 3
of this AD. Do all applicable corrective actions specified in Table
3 of this AD before further flight. Doing the applicable action(s)
ends the requirements of paragraphs (g)(1) and (g)(2) of this AD.
Table 3.--Replacement of Input Control Rods, Inspection, and Corrective Action, as Applicable
----------------------------------------------------------------------------------------------------------------
Do the following
For Model-- Identified as-- action(s)-- In accordance with--
----------------------------------------------------------------------------------------------------------------
(i) 737-100, -200, and -200C Groups 1 through 9, Replace both input control Part 2 of the
series airplanes. Configuration 3 in rods of the main rudder Accomplishment
the service bulletin. PCU with new input Instructions of Boeing
control rods. Service Bulletin 737-27-
1252, Revision 3, dated
May 12, 2006.
(ii) 737-300, -400, and -500 Groups 1 through 19, Replace both input control Part 2 of the
series airplanes. Configuration 3 in rods of the main rudder Accomplishment
the service bulletin. PCU with new input Instructions of Boeing
control rods. Service Bulletin 737-27-
1255, Revision 3, dated
May 10, 2006.
(iii) 737-600, -700, -700C, -800, Groups 1 through 20, Replace both input control Part 2 of the
and -900 series airplanes. Configuration 3 in rods of the main rudder Accomplishment
the service bulletin. PCU with new input Instructions of Boeing
control rods, inspect the Service Bulletin 737-27-
input control rod of the 1253, Revision 3, dated
standby rudder PCU to May 12, 2006.
determine if part number
(P/N) 251A3495-1 is
installed, and any
corrective action.
(iv) 737-600, -700, -700C, -800, Group 1 in the Replace both input control The Accomplishment
and -900 series airplanes. service bulletin. rods of the main rudder Instructions of Boeing
PCU and the input control Alert Service Bulletin
rod of the standby rudder 737-27A1279, dated June
PCU with a new input 20, 2006.
control rod(s).
----------------------------------------------------------------------------------------------------------------
For Certain Other Airplanes: Install New Rudder Control System per
Service Information
(h) For airplanes on which the actions required by paragraph (f)
of this AD have not been done before the effective date of this AD:
As of the effective date of this AD, use the applicable service
bulletin specified in Table 4 of this AD to do the actions required
by paragraph (f) of this AD at the time specified in that paragraph.
Table 4.--Service Bulletins for Installation of New Rudder Control
System
------------------------------------------------------------------------
Do the actions
required by paragraph
For model-- Identified as-- (f) of this AD in
accordance with--
------------------------------------------------------------------------
(1) 737-100, -200, and -200C Groups 1 through Part 1 of the
series airplanes. 9, Accomplishment
Configurations 1 Instructions of
and 2 in the Boeing Service
service bulletin. Bulletin 737-27-
1252, Revision 3,
dated May 12, 2006.
(2) 737-300, -400, and -500 Groups 1 through Part 1 of the
series airplanes. 19, Accomplishment
Configurations 1 Instructions of
and 2 in the Boeing Service
service bulletin. Bulletin 737-27-
1255, Revision 3,
dated May 10, 2006.
(3) 737-600, -700, -700C, - Groups 1 through Part 1 of the
800, and -900 series 20, Accomplishment
airplanes. Configurations 1 Instructions of
and 2 in the Boeing Service
service bulletin. Bulletin 737-27-
1253, Revision 3,
dated May 12, 2006.
------------------------------------------------------------------------
(i) Before or concurrently with the requirements of paragraph
(h) of this AD, do the actions in Table 5 of this AD.
[[Page 66480]]
Table 5.--Before/Concurrent Requirements
------------------------------------------------------------------------
In accordance with
Before or concurrently with Do these actions-- the accomplishment
the actions specified in-- instructions of--
------------------------------------------------------------------------
(1) Paragraph (h)(1) of this (i) Remove the Boeing Service
AD. rudder position Bulletin 737-22-
sensor of the 1042, Revision 1,
automatic flight dated April 5,
control system. 1985.
(ii) Replace the Boeing 737 Service
rudder feel and Bulletin 27-1026,
centering assembly dated January 15,
with a new all- 1971.
mechanical unit.
(iii) Install the Boeing Service
rudder pressure Bulletin 737-
reducer and yaw 27A1206, Revision
damper coupler. 3, dated December
14, 2000.
(iv) Install Boeing Service
provisional wires Bulletin 737-27-
for rudder system 1246, Revision 1,
enhancement. dated February 21,
2002.
(v) Replace the P5-3 Boeing Service
panel with a new Bulletin 737-27-
panel. 1263, Revision 1,
dated September 25,
2003.
(vi) Replace the Smiths Aerospace
input lever for the Service Bulletin
auxiliary rudder 1150-27-05A, dated
power control August 28, 2003.
package with a new
input lever.
(2) Paragraph (h)(2) of this (i) Install Boeing Service
AD. provisional wires Bulletin 737-27-
for rudder system 1246, Revision 1,
enhancement. dated February 21,
2002.
(ii) Replace the P5- Boeing Service
3 panel with a new Bulletin 737-27-
panel. 1264, Revision 1,
dated April 3,
2003.
(iii) Install a new Boeing Service
yaw damper coupler. Bulletin 737-
27A1206, Revision
3, dated December
14, 2000.
(iv) Inspect the Boeing Service
trailing edge beam Bulletin 737-55-
on the vertical fin 1052, Revision 1,
and rework if dated August 5,
necessary. 2004.
(v) Replace the Smiths Aerospace
input lever for the Service Bulletin
auxiliary rudder 1150-27-05A, dated
power control August 28, 2003.
package with a new
input lever.
(3) Paragraph (h)(3) of this (i) Install Boeing Service
AD. provisional wires Bulletin 737-27-
for rudder system 1247, Revision 1,
enhancement. dated July 25,
2002.
(ii) Replace the P5- Boeing Service
3 panel with a new Bulletin 737-27-
panel. 1262, dated
December 19, 2002.
(iii) Relocate the Boeing Alert Service
wire bundle routing Bulletin 737-
in the vertical 27A1239, dated
stabilizer. January 11, 2001.
------------------------------------------------------------------------
Parts Installation
(j) As of the effective date of this AD, no person may install
an input control rod, P/N 251A3495-1, on any airplane.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle 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 Sec.
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) Except as provided by paragraph (j) of this AD: AMOCs
approved previously in accordance with AD 2002-20-07 R1 are approved
as AMOCs for the corresponding provisions of paragraphs (f) and (h)
of this AD.
Issued in Renton, Washington, on November 3, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-19227 Filed 11-14-06; 8:45 am]
BILLING CODE 4910-13-P