Airworthiness Directives; Boeing Model 737-800 Series Airplanes, 21083-21086 [E7-7850]
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Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Rules and Regulations
Seattle, Washington 98124–2207, for a copy
of this service information. You may review
copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
TABLE 1.—MATERIAL INCORPORATED
BY REFERENCE
Boeing
Service
Bulletin
Revision
level
777–27–
0034.
777–57–
0054.
777–57A–
0048.
1 ..............
April 20, 2006.
Original ...
February 23, 2006.
1 ..............
June 9, 2005.
Date
Issued in Renton, Washington, on April 17,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–7853 Filed 4–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27558; Directorate
Identifier 2007–NM–053–AD; Amendment
39–15036; AD 2007–06–52]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–800 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
pwalker on PROD1PC71 with RULES
AGENCY:
SUMMARY: This document publishes in
the Federal Register an amendment
adopting airworthiness directive (AD)
2007–06–52 that was sent previously to
all known U.S. owners and operators of
Boeing Model 737–800 series airplanes
by individual notices. This AD requires
inspecting spoilers to determine spoiler
position after every landing and after
any rejected takeoff maneuvers. For
airplanes on which any spoiler is found
in the up position with the speedbrake
handle in the down position, this AD
requires replacement of the flight
spoiler actuator with a flight spoiler
actuator having a certain part number.
This AD also requires an operational
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16:27 Apr 27, 2007
Jkt 211001
test of the speedbrake control system
after any maintenance actions that
operate the spoiler system and
replacement of the flight spoiler
actuator if necessary. This AD also
provides for optional terminating action
for those requirements. In addition, this
AD requires you to report to the
manufacturer any spoiler panel that is
found in the up position with the
speedbrake handle in the down
position. This AD results from a report
of seven flight spoiler actuator jams on
Model 737–800 Short Field Performance
airplanes. We are issuing this AD to
detect and correct any spoiler panel that
is found in the up position with the
speedbrake handle in the down
position, which could result in a spoiler
actuator hardover, and could cause the
spoiler surface to jam in the fully
extended position. Two or more
hardover failures of the spoiler surfaces
in the up direction on the same wing,
if undetected prior to takeoff, can cause
significant roll and consequent loss of
control of the airplane.
DATES: This AD becomes effective May
7, 2007 to all persons except those
persons to whom it was made
immediately effective by emergency AD
2007–06–52, issued March 14, 2007,
which contained the requirements of
this amendment.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of May 7, 2007.
We must receive comments on this
AD by June 29, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
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,
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 AD.
FOR FURTHER INFORMATION CONTACT:
Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM–
PO 00000
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21083
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6490; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: On March
14, 2007, we issued emergency AD
2007–06–52, which applies to certain
Boeing Model 737–800 series airplanes.
Background
On March 13, 2007, the FAA issued
emergency AD 2007–06–51 for certain
Boeing Model 737–800 series airplanes.
That AD requires inspecting spoilers to
determine spoiler position after every
landing and after any rejected takeoff
maneuvers. For airplanes on which any
spoiler is found in the up position with
the speedbrake handle in the down
position, that AD requires replacement
of the flight spoiler actuator with a flight
spoiler actuator having a certain part
number. That AD also requires an
operational test of the speedbrake
control system after any maintenance
actions that operate the spoiler system
and replacement of the flight spoiler
actuator if necessary. That AD also
provides for optional terminating action
for those requirements. In addition, that
AD requires you to report to the
manufacturer any spoiler panel that is
found in the up position with the
speedbrake handle in the down
position.
That AD resulted from a report of
seven flight spoiler actuator jams on
Model 737–800 Short Field Performance
(SFP) airplanes. Two reports involved
in-service airplanes that were
discovered during a routine
maintenance walk-around and were
believed to have occurred on the
previous landing during auto
speedbrake extension. Five other reports
occurred during spoiler system testing
at Boeing prior to delivery. An
additional two reports of spoiler
actuator input lever binding were
identified during bench testing after
Boeing began to investigate this issue.
The two in-service failures of flight
spoilers resulted in the spoilers not
retracting after the speedbrake handle
was moved to the DOWN position after
landing, on a Boeing Model 737–800
airplane equipped with an SFP package.
In both of these cases, the spoiler was
discovered in the full-extended position
during a routine maintenance walkaround. The spoiler remained in the
full-extended position after cycling of
the speedbrake handle.
Further investigation revealed that the
spoiler actuator failure is most likely to
occur when the speedbrakes are
deployed on the ground (automatically
or manually) for either a rejected takeoff
or normal landing. The takeoff
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configuration warning will not sound if
any flight spoiler remains extended with
the speedbrake handle in the DOWN
position. The cause of the failure has
been identified as interference within
the actuator main control valve.
This condition, if not corrected, could
result in a spoiler actuator hardover,
which could cause the spoiler surface to
jam in the fully extended position. Two
or more hardover failures of the spoiler
surfaces in the up direction on the same
wing, if undetected prior to takeoff, can
cause significant roll and consequent
loss of control of the airplane.
Actions Since Issuance of Previous AD
Since that AD was issued, we have
become aware of two incorrect part
numbers identified throughout
emergency AD 2007–06–51. The
identified incorrect part numbers do not
exist. The incorrect part numbers were
for the replacement flight spoiler
actuator and the flight spoiler actuator
that may no longer be installed.
In light of this, we have determined
that emergency AD 2007–06–51 must be
superseded to reflect the correct part
numbers.
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Relevant Service Information
We have reviewed Boeing 737 Flight
Crew Operations Manual Bulletin No.
TBC–67, dated March 5, 2007. The
bulletin describes procedures for
inspecting spoilers to determine spoiler
position after landing and after any
rejected takeoff maneuvers. For
airplanes on which any spoiler is found
in the up position with the speedbrake
handle in the down position, the
bulletin specifies to contact
maintenance.
FAA’s Determination and Requirements
of This AD
Since the unsafe condition described
is likely to exist or develop on other
airplanes of the same type design, we
issued emergency AD 2007–06–52 to
detect and correct any spoiler panel that
is found in the up position with the
speedbrake handle in the down
position, which could result in a spoiler
actuator hardover, and could cause the
spoiler surface to jam in the fully
extended position. Two or more
hardover failures of the spoiler surfaces
in the up direction on the same wing,
if undetected prior to takeoff, can cause
significant roll and consequent loss of
control of the airplane. This new AD
supersedes emergency AD 2007–06–51.
This new AD requires the actions
specified in emergency AD 2007–06051,
but corrects certain part numbers. This
AD requires accomplishing the actions
specified in the service information
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16:27 Apr 27, 2007
Jkt 211001
described previously, except as
described in ‘‘Differences Between This
AD and the Service Information.’’
We found that immediate corrective
action was required; therefore, notice
and opportunity for prior public
comment thereon were impracticable
and contrary to the public interest, and
good cause existed to make the AD
effective immediately by individual
notices issued on March 14, 2007, to all
known U.S. owners and operators of
Boeing Model 737–800 series airplanes.
These conditions still exist, and the AD
is hereby published in the Federal
Register as an amendment to section
39.13 of the Federal Aviation
Regulations (14 CFR 39.13) to make it
effective to all persons.
Differences Between This AD and the
Service Information
In addition to the inspection specified
in the service information, this AD also
requires that, after any maintenance
action that operates the spoiler system,
the ‘‘Speedbrake Control System
Operational Test’’ specified in Chapter
27–62–00 of the Boeing 737–600/700/
800/900 Aircraft Maintenance Manual
(AMM) be accomplished. This AD also
specifies that the Master Minimum
Equipment List Item 27–7, ‘‘Auto Speed
Brake System,’’ is no longer applicable
to Model 737–800 series airplanes
equipped with an SFP package. This AD
also provides an optional terminating
action of installing flight spoiler
actuator, part number (P/N)
P665A0001–01 or higher dash number,
in all eight flight spoiler positions.
Although the service information
specifies that operators may contact
maintenance for disposition if any
spoiler remains in the up position with
the speedbrake handle in the down
position, this AD requires operators to
replace the flight spoiler actuator with
a flight spoiler actuator, having P/N
P665A0001–01 or higher dash number,
using a method approved by the FAA.
Operators should note that the service
information specifies doing an
inspection. However, this AD requires
doing a ‘‘visual check,’’ which may be
done by qualified ground personnel or
flightcrew. We have determined that
these visual checks may be properly
performed by flightcrew because the
checks do not require tools, precision
measuring equipment, training, or pilot
logbook endorsements, or the use of or
reference to technical data that are not
contained in the body of the AD.
Interim Action
We consider this AD interim action.
We are currently considering requiring
the replacement of the flight spoiler
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actuator, which will constitute
terminating action for the visual checks
and operational tests required by this
AD action.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–27558; Directorate Identifier
2007–NM–053–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
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 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.
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
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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 AD will
not have federalism implications under
Executive Order 13132. This 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.
The FAA has determined that this
regulation is an emergency regulation
that must be issued immediately to
correct an unsafe condition in aircraft,
and that it is not a ‘‘significant
regulatory action’’ under Executive
Order 12866. It has been determined
further that this action involves an
emergency regulation under DOT
Regulatory Policies and Procedures (44
FR 11034, February 26, 1979). If this
emergency regulation is later deemed
significant under DOT Regulatory
Policies and Procedures, we will
prepare a final regulatory evaluation
and place it in the AD Docket. See the
ADDRESSES section for a location to
examine the regulatory evaluation, if
filed.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
pwalker on PROD1PC71 with RULES
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
2007–06–52 Boeing: Amendment 39–15036.
Docket No. FAA–2007–27558;
Directorate Identifier 2007–NM–053–AD.
VerDate Aug<31>2005
16:27 Apr 27, 2007
Jkt 211001
Effective Date
(a) This AD becomes effective May 7, 2007,
to all persons except those persons to whom
it was made immediately effective by
emergency AD 2007–06–52, issued on March
14, 2007, which contained the requirements
of this amendment.
Affected ADs
(b) This AD supersedes emergency AD
2007–06–51, issued March 13, 2007.
Applicability
(c) This AD applies to the Boeing Model
737–800 series airplanes, certificated in any
category, serial numbers 32685, 34277
through 34281 inclusive, 34474, 34475,
34654 through 34656 inclusive, 34690,
34948, 34949, 35091 through 35093
inclusive, 35103, 35134, 35176 through
35183 inclusive, 35330, 35331, 35558, 35559,
and 36323 through 36328 inclusive.
Unsafe Condition
(d) This AD results from a report of seven
flight spoiler actuator jams on Model 737–
800 Short Field Performance (SFP) airplanes.
The cause of the failure has been identified
as interference within the actuator main
control valve. We are issuing this AD to
detect and correct any spoiler panel that is
found in the up position with the speedbrake
handle in the down position, which could
result in a spoiler actuator hardover, and
could cause the spoiler surface to jam in the
fully extended position. Two or more
hardover failures of the spoiler surfaces in
the up direction on the same wing, if
undetected prior to takeoff, can cause
significant roll 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.
Visual Check and Corrective Action
(f) Within 24 clock hours after the effective
date of this AD, do the actions specified in
paragraphs (f)(1), (f)(2), and (f)(3) of this AD,
as applicable. The visual checks required by
paragraphs (f)(1) and (f)(2) of this AD may be
performed by qualified personnel or
flightcrew, and must be entered into the
aircraft records showing compliance with
this AD in accordance with 14 CFR 43.9(b)
and 14 CFR 121.363 and 121.380.
(1) After every landing, visually check the
spoilers to determine spoiler position, in
accordance with Boeing 737 Flight Crew
Operations Manual Bulletin No. TBC–67,
dated March 5, 2007.
(i) If all spoilers are determined to be
properly stowed, no further action is required
by this paragraph.
(ii) If any spoiler is found to be improperly
stowed (in the up position with the
speedbrake handle in the down position),
before further flight, replace the flight spoiler
actuator with a flight spoiler actuator, having
part number (P/N) P665A0001–01 or higher
dash number, in accordance with a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA. The ‘‘Flight
PO 00000
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21085
Spoiler Actuator Removal’’ task and the
‘‘Flight Spoiler Actuator Installation’’ task in
Chapter 27–61–51 of the Boeing 737–600/
700/800/900 Aircraft Maintenance Manual
(AMM) are approved methods for the
replacement (removal and installation) of the
flight spoiler actuator.
(2) After any rejected takeoff maneuver, do
the visual check specified in paragraph (f)(1)
of this AD.
(3) After any maintenance action that
operates the spoiler system, do an
operational test of the speedbrake control
system in accordance with a method
approved by the Manager, Seattle ACO, FAA.
The ‘‘Speedbrake Control System Operational
Test’’ specified in Chapter 27–62–00 of the
Boeing 737–600/700/800/900 AMM is one
approved method for the operational test of
the speedbrake control system. If any spoiler
panel is found to be fully extended with the
speedbrake handle down, or if any spoiler
panel is found fully retracted when the
speedbrake handle is up, before further flight,
replace the flight spoiler actuator in
accordance with the actions specified in
paragraph (f)(1)(ii) of this AD.
Master Minimum Equipment List Item
(g) As of the effective date of this AD, the
Master Minimum Equipment List Item 27–7,
‘‘Auto Speed Brake System,’’ is no longer
applicable to Model 737–800 series airplanes
equipped with an SFP package.
Optional Terminating Action
(h) Installation of flight spoiler actuator, P/
N P665A0001–01 or higher dash number, in
all eight flight spoiler positions ends the
requirements of paragraph (f) of this AD.
Reporting
(i) If any spoiler is found to be improperly
stowed during any visual check required by
this AD, at the applicable time specified in
paragraphs (i)(1) and (i)(2) of this AD, report
the following information electronically to
Boeing using the established Boeing
Communications System (BCS): Airplane
serial number, jam position, spoiler panel
number or wing position of the spoiler that
jammed, date of visual check, and flight
hours accumulated on the airplane.
(1) For visual checks done before the
effective date of this AD: Within 7 days after
the effective date of this AD.
(2) For visual checks done after the
effective date of this AD: Within 7 days after
doing the inspection.
Parts Installation
(j) As of the effective date of this AD, no
person may install a flight spoiler actuator,
having P/N P665A0001–00, on any airplane.
Special Flight Permit
(k) Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
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(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.
Material Incorporated by Reference
(m) You must use Boeing 737 Flight Crew
Operations Manual Bulletin No. TBC–67,
dated March 5, 2007, to perform the actions
that are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register approved the incorporation
by reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207,
for a copy of this service information. You
may review copies at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html.
Issued in Renton, Washington, on April 18,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–7850 Filed 4–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27342 Directorate
Identifier 2007–CE–014–AD; Amendment
39–15037; AD 2007–09–05]
RIN 2120–AA64
Airworthiness Directives; APEX
Aircraft Model CAP 10 B Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
pwalker on PROD1PC71 with RULES
AGENCY:
A CAP10B aircraft experienced a reduced
elevator deflection by about 13° due to an
incorrect routing of the Push To Talk (PTT)
wire bundle and improperly secured
16:27 Apr 27, 2007
Jkt 211001
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective June
4, 2007.
On June 4, 2007 the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Sarjapur Nagarajan, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4145; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. The streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decisionmaking
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This AD references the MCAI and
related service information that we
considered in forming the engineering
basis to correct the unsafe condition.
The AD contains text copied from the
MCAI and for this reason might not
follow our plain language principles.
Discussion
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
VerDate Aug<31>2005
connectors which impeded the complete and
free movement of the control stick.
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on March 9, 2007 (72 FR
10624). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
A CAP10B aircraft experienced a reduced
elevator deflection by about 13° due to an
incorrect routing of the Push To Talk (PTT)
wire bundle and improperly secured
connectors which impeded the complete and
free movement of the control stick.
Actions specified in this AD are intended
to inspect, detect and correct any
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
discrepancy on the PTT electrical circuit
connectors and wires that could lead to a
reduction of the control stick movements.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a note within the AD.
Costs of Compliance
We estimate that this AD will affect
31 products of U.S. registry. We also
estimate that it will take about 1 workhour per product to comply with basic
requirements of this AD. The average
labor rate is $80 per work-hour. Based
on these figures, we estimate the cost of
this AD to the U.S. operators to be
$2,480 or $80 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 3 work-hours and require parts
costing $90, for a cost of $330 per
product. We have no way of
determining the number of products
that may need these actions.
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
E:\FR\FM\30APR1.SGM
30APR1
]]>Agencies
[Federal Register Volume 72, Number 82 (Monday, April 30, 2007)]
[Rules and Regulations]
[Pages 21083-21086]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-7850]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27558; Directorate Identifier 2007-NM-053-AD;
Amendment 39-15036; AD 2007-06-52]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-800 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: This document publishes in the Federal Register an amendment
adopting airworthiness directive (AD) 2007-06-52 that was sent
previously to all known U.S. owners and operators of Boeing Model 737-
800 series airplanes by individual notices. This AD requires inspecting
spoilers to determine spoiler position after every landing and after
any rejected takeoff maneuvers. For airplanes on which any spoiler is
found in the up position with the speedbrake handle in the down
position, this AD requires replacement of the flight spoiler actuator
with a flight spoiler actuator having a certain part number. This AD
also requires an operational test of the speedbrake control system
after any maintenance actions that operate the spoiler system and
replacement of the flight spoiler actuator if necessary. This AD also
provides for optional terminating action for those requirements. In
addition, this AD requires you to report to the manufacturer any
spoiler panel that is found in the up position with the speedbrake
handle in the down position. This AD results from a report of seven
flight spoiler actuator jams on Model 737-800 Short Field Performance
airplanes. We are issuing this AD to detect and correct any spoiler
panel that is found in the up position with the speedbrake handle in
the down position, which could result in a spoiler actuator hardover,
and could cause the spoiler surface to jam in the fully extended
position. Two or more hardover failures of the spoiler surfaces in the
up direction on the same wing, if undetected prior to takeoff, can
cause significant roll and consequent loss of control of the airplane.
DATES: This AD becomes effective May 7, 2007 to all persons except
those persons to whom it was made immediately effective by emergency AD
2007-06-52, issued March 14, 2007, which contained the requirements of
this amendment.
The incorporation by reference of a certain publication listed in
the AD is approved by the Director of the Federal Register as of May 7,
2007.
We must receive comments on this AD by June 29, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this 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, 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 AD.
FOR FURTHER INFORMATION CONTACT: Kelly McGuckin, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6490; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: On March 14, 2007, we issued emergency AD
2007-06-52, which applies to certain Boeing Model 737-800 series
airplanes.
Background
On March 13, 2007, the FAA issued emergency AD 2007-06-51 for
certain Boeing Model 737-800 series airplanes. That AD requires
inspecting spoilers to determine spoiler position after every landing
and after any rejected takeoff maneuvers. For airplanes on which any
spoiler is found in the up position with the speedbrake handle in the
down position, that AD requires replacement of the flight spoiler
actuator with a flight spoiler actuator having a certain part number.
That AD also requires an operational test of the speedbrake control
system after any maintenance actions that operate the spoiler system
and replacement of the flight spoiler actuator if necessary. That AD
also provides for optional terminating action for those requirements.
In addition, that AD requires you to report to the manufacturer any
spoiler panel that is found in the up position with the speedbrake
handle in the down position.
That AD resulted from a report of seven flight spoiler actuator
jams on Model 737-800 Short Field Performance (SFP) airplanes. Two
reports involved in-service airplanes that were discovered during a
routine maintenance walk-around and were believed to have occurred on
the previous landing during auto speedbrake extension. Five other
reports occurred during spoiler system testing at Boeing prior to
delivery. An additional two reports of spoiler actuator input lever
binding were identified during bench testing after Boeing began to
investigate this issue.
The two in-service failures of flight spoilers resulted in the
spoilers not retracting after the speedbrake handle was moved to the
DOWN position after landing, on a Boeing Model 737-800 airplane
equipped with an SFP package. In both of these cases, the spoiler was
discovered in the full-extended position during a routine maintenance
walk-around. The spoiler remained in the full-extended position after
cycling of the speedbrake handle.
Further investigation revealed that the spoiler actuator failure is
most likely to occur when the speedbrakes are deployed on the ground
(automatically or manually) for either a rejected takeoff or normal
landing. The takeoff
[[Page 21084]]
configuration warning will not sound if any flight spoiler remains
extended with the speedbrake handle in the DOWN position. The cause of
the failure has been identified as interference within the actuator
main control valve.
This condition, if not corrected, could result in a spoiler
actuator hardover, which could cause the spoiler surface to jam in the
fully extended position. Two or more hardover failures of the spoiler
surfaces in the up direction on the same wing, if undetected prior to
takeoff, can cause significant roll and consequent loss of control of
the airplane.
Actions Since Issuance of Previous AD
Since that AD was issued, we have become aware of two incorrect
part numbers identified throughout emergency AD 2007-06-51. The
identified incorrect part numbers do not exist. The incorrect part
numbers were for the replacement flight spoiler actuator and the flight
spoiler actuator that may no longer be installed.
In light of this, we have determined that emergency AD 2007-06-51
must be superseded to reflect the correct part numbers.
Relevant Service Information
We have reviewed Boeing 737 Flight Crew Operations Manual Bulletin
No. TBC-67, dated March 5, 2007. The bulletin describes procedures for
inspecting spoilers to determine spoiler position after landing and
after any rejected takeoff maneuvers. For airplanes on which any
spoiler is found in the up position with the speedbrake handle in the
down position, the bulletin specifies to contact maintenance.
FAA's Determination and Requirements of This AD
Since the unsafe condition described is likely to exist or develop
on other airplanes of the same type design, we issued emergency AD
2007-06-52 to detect and correct any spoiler panel that is found in the
up position with the speedbrake handle in the down position, which
could result in a spoiler actuator hardover, and could cause the
spoiler surface to jam in the fully extended position. Two or more
hardover failures of the spoiler surfaces in the up direction on the
same wing, if undetected prior to takeoff, can cause significant roll
and consequent loss of control of the airplane. This new AD supersedes
emergency AD 2007-06-51. This new AD requires the actions specified in
emergency AD 2007-06051, but corrects certain part numbers. This AD
requires accomplishing the actions specified in the service information
described previously, except as described in ``Differences Between This
AD and the Service Information.''
We found that immediate corrective action was required; therefore,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual notices
issued on March 14, 2007, to all known U.S. owners and operators of
Boeing Model 737-800 series airplanes. These conditions still exist,
and the AD is hereby published in the Federal Register as an amendment
to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to
make it effective to all persons.
Differences Between This AD and the Service Information
In addition to the inspection specified in the service information,
this AD also requires that, after any maintenance action that operates
the spoiler system, the ``Speedbrake Control System Operational Test''
specified in Chapter 27-62-00 of the Boeing 737-600/700/800/900
Aircraft Maintenance Manual (AMM) be accomplished. This AD also
specifies that the Master Minimum Equipment List Item 27-7, ``Auto
Speed Brake System,'' is no longer applicable to Model 737-800 series
airplanes equipped with an SFP package. This AD also provides an
optional terminating action of installing flight spoiler actuator, part
number (P/N) P665A0001-01 or higher dash number, in all eight flight
spoiler positions.
Although the service information specifies that operators may
contact maintenance for disposition if any spoiler remains in the up
position with the speedbrake handle in the down position, this AD
requires operators to replace the flight spoiler actuator with a flight
spoiler actuator, having P/N P665A0001-01 or higher dash number, using
a method approved by the FAA.
Operators should note that the service information specifies doing
an inspection. However, this AD requires doing a ``visual check,''
which may be done by qualified ground personnel or flightcrew. We have
determined that these visual checks may be properly performed by
flightcrew because the checks do not require tools, precision measuring
equipment, training, or pilot logbook endorsements, or the use of or
reference to technical data that are not contained in the body of the
AD.
Interim Action
We consider this AD interim action. We are currently considering
requiring the replacement of the flight spoiler actuator, which will
constitute terminating action for the visual checks and operational
tests required by this AD action.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2007-
27558; Directorate Identifier 2007-NM-053-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
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 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.
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
[[Page 21085]]
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 AD will not have federalism
implications under Executive Order 13132. This 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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If this
emergency regulation is later deemed significant under DOT Regulatory
Policies and Procedures, we will prepare a final regulatory evaluation
and place it in the AD Docket. See the ADDRESSES section for a location
to examine the regulatory evaluation, if filed.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2007-06-52 Boeing: Amendment 39-15036. Docket No. FAA-2007-27558;
Directorate Identifier 2007-NM-053-AD.
Effective Date
(a) This AD becomes effective May 7, 2007, to all persons except
those persons to whom it was made immediately effective by emergency
AD 2007-06-52, issued on March 14, 2007, which contained the
requirements of this amendment.
Affected ADs
(b) This AD supersedes emergency AD 2007-06-51, issued March 13,
2007.
Applicability
(c) This AD applies to the Boeing Model 737-800 series
airplanes, certificated in any category, serial numbers 32685, 34277
through 34281 inclusive, 34474, 34475, 34654 through 34656
inclusive, 34690, 34948, 34949, 35091 through 35093 inclusive,
35103, 35134, 35176 through 35183 inclusive, 35330, 35331, 35558,
35559, and 36323 through 36328 inclusive.
Unsafe Condition
(d) This AD results from a report of seven flight spoiler
actuator jams on Model 737-800 Short Field Performance (SFP)
airplanes. The cause of the failure has been identified as
interference within the actuator main control valve. We are issuing
this AD to detect and correct any spoiler panel that is found in the
up position with the speedbrake handle in the down position, which
could result in a spoiler actuator hardover, and could cause the
spoiler surface to jam in the fully extended position. Two or more
hardover failures of the spoiler surfaces in the up direction on the
same wing, if undetected prior to takeoff, can cause significant
roll 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.
Visual Check and Corrective Action
(f) Within 24 clock hours after the effective date of this AD,
do the actions specified in paragraphs (f)(1), (f)(2), and (f)(3) of
this AD, as applicable. The visual checks required by paragraphs
(f)(1) and (f)(2) of this AD may be performed by qualified personnel
or flightcrew, and must be entered into the aircraft records showing
compliance with this AD in accordance with 14 CFR 43.9(b) and 14 CFR
121.363 and 121.380.
(1) After every landing, visually check the spoilers to
determine spoiler position, in accordance with Boeing 737 Flight
Crew Operations Manual Bulletin No. TBC-67, dated March 5, 2007.
(i) If all spoilers are determined to be properly stowed, no
further action is required by this paragraph.
(ii) If any spoiler is found to be improperly stowed (in the up
position with the speedbrake handle in the down position), before
further flight, replace the flight spoiler actuator with a flight
spoiler actuator, having part number (P/N) P665A0001-01 or higher
dash number, in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA. The ``Flight
Spoiler Actuator Removal'' task and the ``Flight Spoiler Actuator
Installation'' task in Chapter 27-61-51 of the Boeing 737-600/700/
800/900 Aircraft Maintenance Manual (AMM) are approved methods for
the replacement (removal and installation) of the flight spoiler
actuator.
(2) After any rejected takeoff maneuver, do the visual check
specified in paragraph (f)(1) of this AD.
(3) After any maintenance action that operates the spoiler
system, do an operational test of the speedbrake control system in
accordance with a method approved by the Manager, Seattle ACO, FAA.
The ``Speedbrake Control System Operational Test'' specified in
Chapter 27-62-00 of the Boeing 737-600/700/800/900 AMM is one
approved method for the operational test of the speedbrake control
system. If any spoiler panel is found to be fully extended with the
speedbrake handle down, or if any spoiler panel is found fully
retracted when the speedbrake handle is up, before further flight,
replace the flight spoiler actuator in accordance with the actions
specified in paragraph (f)(1)(ii) of this AD.
Master Minimum Equipment List Item
(g) As of the effective date of this AD, the Master Minimum
Equipment List Item 27-7, ``Auto Speed Brake System,'' is no longer
applicable to Model 737-800 series airplanes equipped with an SFP
package.
Optional Terminating Action
(h) Installation of flight spoiler actuator, P/N P665A0001-01 or
higher dash number, in all eight flight spoiler positions ends the
requirements of paragraph (f) of this AD.
Reporting
(i) If any spoiler is found to be improperly stowed during any
visual check required by this AD, at the applicable time specified
in paragraphs (i)(1) and (i)(2) of this AD, report the following
information electronically to Boeing using the established Boeing
Communications System (BCS): Airplane serial number, jam position,
spoiler panel number or wing position of the spoiler that jammed,
date of visual check, and flight hours accumulated on the airplane.
(1) For visual checks done before the effective date of this AD:
Within 7 days after the effective date of this AD.
(2) For visual checks done after the effective date of this AD:
Within 7 days after doing the inspection.
Parts Installation
(j) As of the effective date of this AD, no person may install a
flight spoiler actuator, having P/N P665A0001-00, on any airplane.
Special Flight Permit
(k) Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
[[Page 21086]]
(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.
Material Incorporated by Reference
(m) You must use Boeing 737 Flight Crew Operations Manual
Bulletin No. TBC-67, dated March 5, 2007, to perform the actions
that are required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the incorporation by
reference of this document in accordance with 5 U.S.C. 552(a) and 1
CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124-2207, for a copy of this service
information. You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call 202-741-6030, or
go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued in Renton, Washington, on April 18, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-7850 Filed 4-27-07; 8:45 am]
BILLING CODE 4910-13-P
