Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, -900, and 900ER Series Airplanes, 22090-22092 [E8-8911]
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22090
Federal Register / Vol. 73, No. 80 / Thursday, April 24, 2008 / Proposed Rules
Applicability
(c) This AD applies to all Boeing Model
737–300, –400, and –500 series airplanes,
certificated in any category.
Unsafe Condition
(d) This AD results from a report of an 18inch crack found in the fuselage skin area
under the blade seals of the nose cap of the
dorsal fin due to previous wear damage, and
additional reports of fuselage skin wear. We
are issuing this AD to prevent discrepancies
of the fuselage skin, which could result in
fatigue cracking due to cabin pressurization
and consequent rapid in-flight
decompression of the airplane fuselage.
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.
mstockstill on PROD1PC66 with PROPOSALS
Restatement of Requirements of AD 2004–
22–05
Repetitive Detailed Inspections
(f) For airplanes specified in either
paragraph (f)(1), (f)(2), (f)(3), or (f)(4) of this
AD: Accomplish a detailed inspection for
discrepancies (wear or cracking) of the
fuselage skin under the dorsal fin assembly
by doing all the actions specified in Boeing
Message Number 1–QXO35, dated October
13, 2004. Repeat the inspection thereafter at
intervals not to exceed 9,000 flight cycles.
Accomplishing all of the applicable actions
specified in paragraph (i) of this AD
terminates the repetitive inspections required
by this paragraph.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(1) For airplanes with line numbers 1001
through 2828 inclusive that have not been
inspected as of November 12, 2004 (the
effective date of AD 2004–22–05), in
accordance with Boeing Service Bulletin
737–55–1057, dated December 12, 1996; or
Revision 1, dated July 22, 1999: Inspect
before the accumulation of 18,000 total flight
cycles, or within 90 days after November 12,
2004, whichever is later.
(2) For airplanes with line numbers 2829
through 3132 inclusive that are not included
in the effectivity of Boeing Service Bulletin
737–55–1057, dated December 12, 1996; or
Revision 1, dated July 22, 1999: Inspect
before the accumulation of 18,000 total flight
cycles, or within 90 days after November 12,
2004, whichever is later.
(3) For airplanes with line numbers 1001
through 2828 inclusive that have been
inspected, but not repaired or modified as of
the effective date of this AD, in accordance
with Boeing Service Bulletin 737–55–1057,
dated December 12, 1996; or Revision 1,
dated July 22, 1999: Inspect within 9,000
VerDate Aug<31>2005
16:41 Apr 23, 2008
Jkt 214001
flight cycles after accomplishing the
inspection, or within 90 days after November
12, 2004, whichever is later.
(4) For airplanes with line numbers 1001
through 2828 inclusive that have been
inspected and repaired or modified as of the
effective date of this AD, in accordance with
Boeing Service Bulletin 737–55–1057, dated
December 12, 1996; or Revision 1, dated July
22, 1999: Inspect within 18,000 flight cycles
after accomplishing the repair or
modification, or within 90 days after
November 12, 2004, whichever is later; and
if a repair doubler is installed, before further
flight, inspect the repair doubler for
discrepancies (wear or cracking).
Note 2: Boeing Message Number 1–QXO35,
dated October 13, 2004, references Part I of
Boeing Service Bulletin 737–55–1057,
Revision 1, dated July 22, 1999, as an
additional source of service information for
accomplishing the actions required by
paragraph (f) of this AD.
Repair
(g) If any discrepancy (wear or cracking) is
found during any inspection required by
paragraph (f) of this AD, before further flight,
repair in accordance with a method approved
by the Manager, Seattle Aircraft Certification
Office (ACO), FAA; or using a method
approved in accordance with the procedures
specified in paragraph (1) of this AD.
Reporting Not Required
(h) Although Boeing Message Number 1–
QXO35, dated October 13, 2004, specifies to
report any fuselage skin cracking found
during the detailed inspections, this AD does
not include that requirement.
New Requirements of This AD
New Inspections and Other Specified and
Corrective Actions
(i) At the applicable compliance times
specified in paragraph 1.E. of Boeing Alert
Service Bulletin 737–53A1266, dated August
30, 2007, except as provided by paragraph (j)
of this AD: Do a detailed inspection for any
chafing or crack in the fuselage skin of the
dorsal fin landing and abrasion resistant
coating, do a detailed inspection for damage
to dorsal fin seals, attach clip, and seal
retainer, and do all the applicable other
specified and corrective actions, by
accomplishing all of the applicable actions
specified in the Accomplishment
Instructions of the service bulletin, except as
provided by paragraph (k) of this AD.
Accomplishing all of the applicable actions
specified in this paragraph terminates the
repetitive inspections required by paragraph
(f) of this AD.
Exception to Compliance Times
(j) Where Boeing Alert Service Bulletin
737–53A1266, dated August 30, 2007,
specifies counting the compliance time from
‘‘* * * the date on the service bulletin,’’ this
AD requires counting the compliance time
from the effective date of this AD.
Exception to Corrective Actions
(k) If any damage is found aft of body
station 908 during any inspection required by
this AD, and Boeing Alert Service Bulletin
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Frm 00026
Fmt 4702
Sfmt 4702
737–53A1266, dated August 30, 2007,
specifies to contact Boeing for appropriate
action: Before further flight, repair the
fuselage skin using a method approved in
accordance with the procedures specified in
paragraph (l) of this AD.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, Seattle Aircraft
Certification Office, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 2004–22–05 are
approved as AMOCs for the corresponding
provisions of paragraphs (f) and (g) of this
AD.
Issued in Renton, Washington, on April 15,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–8913 Filed 4–23–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0413; Directorate
Identifier 2008–NM–003–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, –800,
–900, and 900ER Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Boeing Model 737–600, –700, –700C,
–800, –900, and 900ER series airplanes.
This proposed AD would require
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Federal Register / Vol. 73, No. 80 / Thursday, April 24, 2008 / Proposed Rules
replacing the pushrods for the left and
right elevator tab control mechanisms
with new, improved pushrods. This
proposed AD results from a report of a
rod end fracture on a rudder Power
Control Unit (PCU) control rod, which
is similar to the ones used for the
elevator tab pushrods. Analysis revealed
that the fractured rod end had an
incorrect hardness, which had probably
occurred during the manufacture of the
control rod. We are proposing this AD
to prevent fracture of the elevator tab
pushrod ends, which could result in
excessive in-flight vibrations of the
elevator tab, possible loss of the elevator
tab, and consequent loss of
controllability of the airplane.
We must receive comments on
this proposed AD by June 9, 2008.
DATES:
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
mstockstill on PROD1PC66 with PROPOSALS
FOR FURTHER INFORMATION CONTACT:
Tamara Anderson, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6421; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
VerDate Aug<31>2005
16:41 Apr 23, 2008
Jkt 214001
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0413; Directorate Identifier
2008–NM–003–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received a report of a rod
end fracture on a rudder Power Control
Unit (PCU) control rod, which is similar
to the ones used for the elevator tab
pushrods. An operator found a broken
rudder PCU control rod during heavy
maintenance of a Model 737–800
airplane. Analysis revealed that the
fractured rod end had an incorrect
hardness, which had probably occurred
during the manufacture of the control
rod. During the manufacturing process,
specific areas of the control rods are to
be masked off to prevent the application
of the heat treatment/carburization
process in those areas. But at different
site locations of the supplier, the heat
treatment/carburization process was
done differently, which resulted in the
application of the heat treatment/
carburization process of some control
rods in incorrect areas. This caused an
incorrect hardness of the hollow shanks
of the rod ends, and resulted in the
occurrence of cracks at the time of
manufacture. Further analysis revealed
that all control rods made by the
supplier were also affected by the
incorrect manufacturing procedure.
Subsequently, an improved design of
the control rod was developed to change
from hollow shank rod ends to solid
shank rod ends, which would prevent
the problems with the heat treatment/
carburization process during
manufacture. Fracture of the elevator tab
pushrod ends could result in excessive
in-flight vibrations of the elevator tab,
possible loss of the elevator tab, and
consequent loss of controllability of the
airplane.
PO 00000
Frm 00027
Fmt 4702
Sfmt 4702
22091
Relevant Service Information
We have reviewed Boeing Special
Attention Service Bulletin 737–27–
1284, dated November 28, 2007. The
service bulletin describes procedures for
replacing the pushrods for the left and
right elevator tab control mechanism
with new, improved pushrods. The
service bulletin specifies doing the
replacement within 4 years after the
date on the service bulletin.
Other Related Rulemaking
On January 29, 2003, the FAA issued
AD 2003–03–22, amendment 39–13047
(68 FR 5819, February 5, 2003), which
applies to certain Boeing Model 737–
600, –700, –700C, –800, and –900 series
airplanes. AD 2003–03–22 requires
accomplishing the modification in
accordance with Boeing Alert Service
Bulletin 737–55A1080, dated September
19, 2002, and Service Bulletin 737–27–
1284 specifies prior or concurrent
accomplishment of Service Bulletin
737–55A1080. AD 2003–03–22 requires
installing speedbrake limitation
placards in the flight compartment, and
revising the Limitations Section of the
Airplane Flight Manual to ensure the
flightcrew is advised not to extend the
speedbrake lever beyond the flight
detent. For Model 737–600, –700,
–700C, –800 series airplanes having line
numbers 1 through 1174 inclusive, AD
2003–03–22 requires modifying the
elevator and elevator tab assembly
before the accumulation of 18,000 total
flight cycles, or within 2 years after
March 12, 2003, whichever occurs first.
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design. This proposed AD would
require accomplishing the actions
specified in the service information
described previously.
Costs of Compliance
We estimate that this proposed AD
would affect 715 airplanes of U.S.
registry. We also estimate that it would
take about 4 work-hours per product to
comply with this proposed AD. The
average labor rate is $80 per work-hour.
Required parts would cost about $8,036
per product. Based on these figures, we
estimate the cost of this proposed AD to
the U.S. operators to be $5,974,540, or
$8,356 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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22092
Federal Register / Vol. 73, No. 80 / Thursday, April 24, 2008 / Proposed Rules
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 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 this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), and
3. 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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
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:
mstockstill on PROD1PC66 with PROPOSALS
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 AD:
VerDate Aug<31>2005
16:41 Apr 23, 2008
Jkt 214001
Boeing: Docket No. FAA–2008–0413;
Directorate Identifier 2008–NM–003–AD.
Comments Due Date
(a) We must receive comments by June 9,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737–
600, –700, –700C, –800, –900, and 900ER
series airplanes, certificated in any category;
line numbers 1 through 2196 inclusive.
Unsafe Condition
(d) This AD results from a report of a rod
end fracture on rudder Power Control Unit
(PCU) control rod, which is similar to the
ones used for the elevator tab pushrods.
Analysis revealed that the fractured rod end
had an incorrect hardness, which had
probably occurred during the manufacture of
the control rod. We are issuing this AD to
prevent fracture of the elevator tab pushrod
ends, which could result in excessive inflight vibrations of the elevator tab, possible
loss of the elevator tab, and consequent loss
of controllability of the airplane.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Pushrod Replacement
(f) At the time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 737–27–1284, dated
November 28, 2007; except, where the
service bulletin specifies a compliance time
after the date on the service bulletin, this AD
requires compliance within the specified
compliance time after the effective date of
this AD: Replace the pushrods for the left and
right elevator tab control mechanisms with
new, improved pushrods by doing all the
actions in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–27–
1284, dated November 28, 2007.
Parts Installation
(g) As of the effective date of this AD, no
person may install a pushrod assembly, part
number 65–45166–24, on any airplane.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Tamara Anderson, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
917–6421; fax (425) 917–6590; has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
PO 00000
Frm 00028
Fmt 4702
Sfmt 4702
Office (FSDO), or lacking a PI, your local
FSDO.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane.
Issued in Renton, Washington, on April 15,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–8911 Filed 4–23–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Highway Administration
23 CFR Part 924
[FHWA Docket No. FHWA–2008–0009]
RIN 2125–AF25
Highway Safety Improvement Program
Federal Highway
Administration (FHWA), DOT.
ACTION: Notice of proposed rule making
(NPRM); request for comments.
AGENCY:
SUMMARY: The purpose of this notice of
proposed amendments is to revise Part
924 to incorporate changes to the
Highway Safety Improvement Program
(HSIP) that resulted from the Safe,
Accountable, Flexible, Efficient
Transportation Equity Act: A Legacy for
Users (SAFETEA–LU), as well as to
reflect changes in the overall program
that have evolved since 23 CFR part 924
was originally written.
DATES: Comments must be received on
or before June 23, 2008.
ADDRESSES: Mail or hand deliver
comments to the U.S. Department of
Transportation, Dockets Management
Facility, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, or submit
electronically at https://
www.regulations.gov or fax comments to
(202) 493–2251. All comments should
include the docket number that appears
in the heading of this document. All
comments received will be available for
examination and copying at the above
address from 9 a.m. to 5 p.m., e.t.,
Monday through Friday, except Federal
holidays. Those desiring notification of
receipt of comments must include a selfaddressed, stamped postcard or may
print the acknowledgment page that
appears after submitting comments
E:\FR\FM\24APP1.SGM
24APP1
]]>Agencies
[Federal Register Volume 73, Number 80 (Thursday, April 24, 2008)]
[Proposed Rules]
[Pages 22090-22092]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-8911]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0413; Directorate Identifier 2008-NM-003-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-600, -700, -700C, -
800, -900, and 900ER Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Boeing Model 737-600, -700, -700C, -800, -900, and 900ER series
airplanes. This proposed AD would require
[[Page 22091]]
replacing the pushrods for the left and right elevator tab control
mechanisms with new, improved pushrods. This proposed AD results from a
report of a rod end fracture on a rudder Power Control Unit (PCU)
control rod, which is similar to the ones used for the elevator tab
pushrods. Analysis revealed that the fractured rod end had an incorrect
hardness, which had probably occurred during the manufacture of the
control rod. We are proposing this AD to prevent fracture of the
elevator tab pushrod ends, which could result in excessive in-flight
vibrations of the elevator tab, possible loss of the elevator tab, and
consequent loss of controllability of the airplane.
DATES: We must receive comments on this proposed AD by June 9, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tamara Anderson, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6421; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0413;
Directorate Identifier 2008-NM-003-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received a report of a rod end fracture on a rudder Power
Control Unit (PCU) control rod, which is similar to the ones used for
the elevator tab pushrods. An operator found a broken rudder PCU
control rod during heavy maintenance of a Model 737-800 airplane.
Analysis revealed that the fractured rod end had an incorrect hardness,
which had probably occurred during the manufacture of the control rod.
During the manufacturing process, specific areas of the control rods
are to be masked off to prevent the application of the heat treatment/
carburization process in those areas. But at different site locations
of the supplier, the heat treatment/carburization process was done
differently, which resulted in the application of the heat treatment/
carburization process of some control rods in incorrect areas. This
caused an incorrect hardness of the hollow shanks of the rod ends, and
resulted in the occurrence of cracks at the time of manufacture.
Further analysis revealed that all control rods made by the supplier
were also affected by the incorrect manufacturing procedure.
Subsequently, an improved design of the control rod was developed to
change from hollow shank rod ends to solid shank rod ends, which would
prevent the problems with the heat treatment/carburization process
during manufacture. Fracture of the elevator tab pushrod ends could
result in excessive in-flight vibrations of the elevator tab, possible
loss of the elevator tab, and consequent loss of controllability of the
airplane.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 737-27-
1284, dated November 28, 2007. The service bulletin describes
procedures for replacing the pushrods for the left and right elevator
tab control mechanism with new, improved pushrods. The service bulletin
specifies doing the replacement within 4 years after the date on the
service bulletin.
Other Related Rulemaking
On January 29, 2003, the FAA issued AD 2003-03-22, amendment 39-
13047 (68 FR 5819, February 5, 2003), which applies to certain Boeing
Model 737-600, -700, -700C, -800, and -900 series airplanes. AD 2003-
03-22 requires accomplishing the modification in accordance with Boeing
Alert Service Bulletin 737-55A1080, dated September 19, 2002, and
Service Bulletin 737-27-1284 specifies prior or concurrent
accomplishment of Service Bulletin 737-55A1080. AD 2003-03-22 requires
installing speedbrake limitation placards in the flight compartment,
and revising the Limitations Section of the Airplane Flight Manual to
ensure the flightcrew is advised not to extend the speedbrake lever
beyond the flight detent. For Model 737-600, -700, -700C, -800 series
airplanes having line numbers 1 through 1174 inclusive, AD 2003-03-22
requires modifying the elevator and elevator tab assembly before the
accumulation of 18,000 total flight cycles, or within 2 years after
March 12, 2003, whichever occurs first.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously.
Costs of Compliance
We estimate that this proposed AD would affect 715 airplanes of
U.S. registry. We also estimate that it would take about 4 work-hours
per product to comply with this proposed AD. The average labor rate is
$80 per work-hour. Required parts would cost about $8,036 per product.
Based on these figures, we estimate the cost of this proposed AD to the
U.S. operators to be $5,974,540, or $8,356 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue
[[Page 22092]]
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 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 this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979), and
3. 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
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 AD:
Boeing: Docket No. FAA-2008-0413; Directorate Identifier 2008-NM-
003-AD.
Comments Due Date
(a) We must receive comments by June 9, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-600, -700, -700C, -800,
-900, and 900ER series airplanes, certificated in any category; line
numbers 1 through 2196 inclusive.
Unsafe Condition
(d) This AD results from a report of a rod end fracture on
rudder Power Control Unit (PCU) control rod, which is similar to the
ones used for the elevator tab pushrods. Analysis revealed that the
fractured rod end had an incorrect hardness, which had probably
occurred during the manufacture of the control rod. We are issuing
this AD to prevent fracture of the elevator tab pushrod ends, which
could result in excessive in-flight vibrations of the elevator tab,
possible loss of the elevator tab, and consequent loss of
controllability of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Pushrod Replacement
(f) At the time specified in paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 737-27-1284, dated
November 28, 2007; except, where the service bulletin specifies a
compliance time after the date on the service bulletin, this AD
requires compliance within the specified compliance time after the
effective date of this AD: Replace the pushrods for the left and
right elevator tab control mechanisms with new, improved pushrods by
doing all the actions in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 737-27-
1284, dated November 28, 2007.
Parts Installation
(g) As of the effective date of this AD, no person may install a
pushrod assembly, part number 65-45166-24, on any airplane.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Tamara Anderson, Aerospace Engineer, Airframe Branch,
ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6421; fax (425) 917-6590;
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane.
Issued in Renton, Washington, on April 15, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-8911 Filed 4-23-08; 8:45 am]
BILLING CODE 4910-13-P
