Airworthiness Directives; Boeing Model 737-800 Series Airplanes, 40226-40230 [E7-13979]
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Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2007–15–02 Bombardier, Inc. (Formerly
Canadair): Amendment 39–15131.
Docket No. FAA–2006–25779;
Directorate Identifier 2006–NM–088–AD.
Effective Date
(a) This AD becomes effective August 28,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Bombardier
Model CL–600–2B19 (Regional Jet Series 100
& 440) airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a report that data
collected from in-service airplanes show that
approximately 19 percent of aileron backlash
checks conducted at 4,000-flight-hour
intervals reveal that aileron backlash wear
limits are being exceeded. We are issuing this
AD to prevent exceeded backlashes in both
aileron power control units (PCUs), which, if
accompanied by the failure of the flutter
damper, could result in aileron vibration/
flutter and reduced controllability of the
airplane.
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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.
Revision of the Maintenance Requirements
Manual (MRM)
(f) Within 60 days after the effective date
of this AD, revise the Canadair Regional Jet
MRM CSP A–053 by doing the actions
specified in paragraphs (f)(1) and (f)(2) of this
AD. When the tasks specified in Canadair
Regional Jet Temporary Revisions 2A–20,
dated March 13, 2006; and 1–2–33, dated
October 27, 2005; are included in the general
revisions of the MRM, the general revisions
may be inserted in the MRM, and these
temporary revisions may be removed.
(1) Revise the Certification Maintenance
Requirements section of the Canadair
Regional Jet MRM to include Tasks C27–10–
105–06 and C27–10–105–05, as specified in
Canadair Regional Jet Temporary Revision
2A–20, dated March 13, 2006, to Part 2,
Appendix A—Certification Maintenance
Requirements, of the Canadair Regional Jet
MRM CSP A–053.
(2) Revise the Maintenance Review Board
Report for Section 2—Systems and
Powerplant Program, of Part 1 of the
Canadair Regional Jet MRM CSP A–053, to
include the task interval for Task 27–11–00–
09, as specified in Canadair Regional Jet
Temporary Revision 1–2–33, dated October
27, 2005. Incorporating Revision 10, dated
May 27, 2005, of the Canadair Regional Jet
Maintenance Review Board Report for
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Section 2—Systems and Powerplant Program
of the Canadair Regional Jet MRM CSP A–053
is one approved method for including the
task interval specified in Canadair Regional
Jet Temporary Revision 1–2–33. After the
task interval has been incorporated into the
MRM, no alternative aileron backlash check
interval in excess of 2,000 flight hours may
be approved, except as specified in
paragraphs (g) and (h) of this AD.
Phase-In Schedule for Initial Inspection
Specified in MRM Revisions
(g) For airplanes with more than 1,000
flight hours but less than 3,000 flight hours
since the last aileron backlash check
specified in Task 27–11–00–09 was
accomplished, as of the effective date of this
AD: Within 1,000 flight hours after the
effective date of this AD, do the next aileron
backlash check in accordance with Task 27–
11–00–09, as specified in Canadair Regional
Jet Temporary Revision 1–2–33, dated
October 27, 2005.
(h) For airplanes with 3,000 flight hours or
more since the last aileron backlash check
specified in Task 27–11–00–09 was
accomplished, as of the effective date of this
AD: Within 4,000 flight hours after the last
aileron backlash check, do the next aileron
backlash check in accordance with Task 27–
11–00–09, as specified in Canadair Regional
Jet Temporary Revision 1–2–33, dated
October 27, 2005.
One Approved Method for Task C27–10–
105–06
(i) For airplanes without access to ground
support equipment necessary to do the PCU
internal leakage functional check, as
specified in Task C27–10–105–06 specified
in paragraph (f)(1) of this AD: Doing the
aileron PCU internal leakage check in
accordance with Task 27–11–00–220–803 of
Chapter 27–11–00 of the Canadair Regional
Jet Aircraft Maintenance Manual at intervals
not to exceed 4,000 flight hours is one
approved method for accomplishing Task
C27–10–105–06, and is acceptable for up to
12 months after the effective date of this AD.
Thereafter, the check must be done in
accordance with Task C27–10–105–06 as
specified in paragraph (f)(1) of this AD at a
repetitive interval not to exceed that
specified in the task.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, New York Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(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.
Related Information
(k) Canadian airworthiness directive CF–
2006–04, dated March 22, 2006, also
addresses the subject of this AD.
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Material Incorporated by Reference
(l) You must use Canadair Regional Jet
Temporary Revision 1–2–33, dated October
27, 2005, to the Canadair Regional Jet
Maintenance Review Manual CSP A–053;
and Canadair Regional Jet Temporary
Revision 2A–20, dated March 13, 2006, to the
Canadair Regional Jet Maintenance Review
Manual CSP A–053; 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 these documents in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087, Station
Centre-ville, Montreal, Quebec H3C 3G9,
Canada, 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/ibrlocations.html.
Issued in Renton, Washington, on July 11,
2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–13983 Filed 7–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28750; Directorate
Identifier 2007–NM–124–AD; Amendment
39–15133; AD 2007–15–04]
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.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to certain Boeing Model
737–800 series airplanes. The existing
AD currently requires inspecting flight
spoilers to determine spoiler position
after every landing and after any
rejected takeoff maneuver. For airplanes
on which any flight spoiler is found in
the up position with the speedbrake
handle in the down position, the
existing AD requires replacing the flight
spoiler actuator with a flight spoiler
actuator having a certain part number.
The existing AD also requires an
operational test of the speedbrake
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Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations
control system after any maintenance
actions that operate the spoiler system,
and replacement of the flight spoiler
actuator if necessary. The existing AD
also provides for optional terminating
action for those requirements. This new
AD requires the previously optional
terminating action. This AD results from
a report of seven flight spoiler actuator
jams on Model 737–800 airplanes
equipped for short field performance
(SFP). The cause of the failure has been
identified as interference within the
actuator main control valve. We are
issuing this AD to prevent operation
with defective flight spoiler actuators,
which could result in a flight spoiler
actuator hardover, and could cause the
flight spoiler surface to jam in the fully
extended position. Two or more
hardover failures of the flight 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
August 8, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of August 8, 2007.
On May 7, 2007 (72 FR 21083, April
30, 2007), the Director of the Federal
Register approved the incorporation by
reference of a certain publication listed
in the AD.
We must receive any comments on
this AD by September 24, 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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
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–
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40227
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6490; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
• Inspecting each flight spoiler after
every landing and after any rejected
takeoff maneuver does not guarantee
that the flight spoiler will function
properly during the next flight.
Discussion
On April 18, 2007, we issued AD
2007–06–52, amendment 39–15036 (72
FR 21083, April 30, 2007). That AD
applies to certain Boeing Model 737–
800 series airplanes. That AD requires
inspecting flight spoilers to determine
spoiler position after every landing and
after any rejected takeoff maneuver. For
airplanes on which any flight 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(s) 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. The actions specified in
that AD are intended 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.
The goal of the actions required by
AD 2007–06–52 is to detect actuators
that might have failed during the
previous flight in order to prevent an
attempted takeoff with extended flight
spoiler(s). We determined that takeoff is
the most critical portion of the flight
profile for this particular failure, but it
is not the only flight profile that could
be affected. Therefore, we are issuing
this new AD for the following reasons:
• Replacing all flight spoiler actuators
is the best method to eliminate the
possibility of this failure.
• The inspections and operational
tests required by AD 2007–06–52 are an
interim solution and cannot detect or
prevent other possible scenarios
involving a failed flight spoiler actuator.
Actions Since AD Was Issued
The preamble to AD 2007–06–52
explains that we consider the
requirements ‘‘interim action’’ and are
considering requiring the replacement
of all eight flight spoiler actuators. We
now have determined that replacement
of the flight spoiler actuators is
necessary, and this AD follows from that
determination. The replacement
actuators correct the interference
condition in the valve assembly,
eliminate possible rate jam conditions,
and ensure continued correct operation
of the flight spoilers. Replacement of all
flight spoiler actuators constitutes
terminating action for the requirements
of AD 2007–06–52.
In addition, paragraph (g) of AD
2007–06–52 also specifies that the
Master Minimum Equipment List
(MMEL) Item 27–7, ‘‘Auto Speed Brake
System,’’ is no longer applicable to
Model 737–800 series airplanes
equipped with an SFP package. Since
we issued AD 2007–06–52, Boeing has
revised MMEL Item 27–7 to accurately
reflect the operational requirements to
account for the degraded performance
when operating a Model 737–800 series
airplane equipped with the SFP package
when it has the auto speed brake system
disabled. Therefore, the requirement in
paragraph (g) of AD 2007–06–52 has not
been restated in this AD. We have relettered the remaining paragraphs
accordingly.
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Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 737–27A1283, dated
April 3, 2007. The service bulletin
describes procedures for installing an
improved SFP actuator for each of the
eight flight spoilers. The installation
includes replacing the SFP actuator,
making sure there is no hydraulic
leakage at the connections to each of the
new, improved SFP actuators, and
completing all adjustments and tests of
each flight spoiler to make sure it
operates correctly. The service bulletin
specifies doing the adjustments and
tests in accordance with the applicable
aircraft maintenance manual. The
service bulletin also specifies returning
each removed flight spoiler SFP actuator
to the vendor for modification. The
service bulletin includes eight
individual work packages for
replacement of each of the eight flight
spoiler actuators to allow flexibility in
accomplishing the service bulletin.
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Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other airplanes of the same type
design. For this reason, we are issuing
this AD to supersede AD 2007–06–52.
This new AD retains certain
requirements of the existing AD. This
AD also requires accomplishing the
actions specified in the service bulletin
described previously, except as
discussed under ‘‘Difference Between
the AD and the Service Bulletin.’’ This
AD allows 120 days from its effective
date to accomplish the required actions.
This amount of time is necessary to
enable operators to obtain sufficient
parts to modify all affected airplanes.
Difference Between the AD and the
Service Bulletin
Operators should note that, although
the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–
27A1283, dated April 3, 2007, describe
procedures for returning parts to the
vendor, this AD does not require that
action.
Change to Alternative Methods of
Compliance (AMOCs) Paragraph
AD 2007–06–52 requires
accomplishing certain actions in
accordance with Boeing 737 Flight Crew
Operations Manual Bulletin No. TBC–
67, dated March 5, 2007. That document
is specific to Boeing operations. Since
we issued AD 2007–06–52, Boeing has
released operator-specific versions of
Bulletin No. TBC–67 for affected
operators of Model 737–800 airplanes
equipped with the SFP package. The
operator-specific documents have been
approved as AMOCs for AD 2007–06–
52. For simplicity, paragraph (f)(1) of
this new AD continues to require
actions in accordance with Bulletin No.
TBC–67. However, paragraph (l)(3) has
been added to this AD to specify that
the existing AMOCs that approve
operator-specific documents continue to
be acceptable.
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Clarification of Terminology
We use the term ‘‘flight spoilers,’’
‘‘flight spoiler actuators,’’ or ‘‘SFP
actuators,’’ in this AD to refer to the
affected spoilers and actuators. There
are ground spoilers on the affected
airplanes, but the ground spoilers have
a different type of actuator and are not
affected by this AD. We have added
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Note 1 to this AD to include this
clarification.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD; therefore, providing notice and
opportunity for public comment before
the AD is issued is impracticable, and
good cause exists to make this AD
effective in less than 30 days.
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–2007–28750; Directorate Identifier
2007–NM–124–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 Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
ground floor of the West Building at the
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,
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Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this 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.
For the reasons discussed above, I
certify that the 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 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, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends part 39 of the Federal
Aviation Regulations (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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
I
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by removing amendment 39–15036 (72
FR 21083, April 30, 2007) and adding
the following new airworthiness
directive (AD):
2007–15–04 Boeing: Docket No. FAA–2007–
28750; Directorate Identifier 2007–NM–
124–AD; Amendment 39–15133.
Effective Date
(a) This AD becomes effective August 8,
2007.
Affected ADs
(b) This AD supersedes AD 2007–06–52.
Applicability
(c) This AD applies to 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 series airplanes equipped for short field
performance (SFP). The cause of the failure
has been identified as interference within the
actuator main control valve. We are issuing
this AD to prevent operation with defective
flight spoiler actuators, 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 flight 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.
Note 1: We use the term ‘‘flight spoilers,’’
‘‘flight spoiler actuators,’’ or ‘‘SFP actuators,’’
in this AD to refer to the affected spoilers and
actuators. There are ground spoilers on the
affected airplanes, but the ground spoilers
have a different type of actuator and are not
affected by this AD.
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Restatement of the Requirements of AD
2007–06–52
Visual Check and Corrective Action
(f) Within 24 clock hours after May 7, 2007
(the effective date of AD 2007–06–52), do the
actions specified in paragraphs (f)(1), (f)(2),
and (f)(3) of this AD, as applicable, until the
action required by paragraph (h) of this AD
is accomplished. 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.
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(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.
Reporting
(g) If any spoiler is found to be improperly
stowed during any visual check required by
this AD, at the applicable time specified in
paragraphs (g)(1) and (g)(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. Doing the
action required by paragraph (h) of this AD
terminates the requirements of this
paragraph.
(1) For visual checks done before May 7,
2007: Within 7 days after May 7, 2007.
(2) For visual checks done after May 7,
2007: Within 7 days after doing the
inspection.
New Requirements of This AD
Terminating Action
(h) Within 120 days after the effective date
of this AD: Install flight spoiler actuator, P/
N P665A0001–01 or higher dash number, in
all eight flight spoiler positions in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–27A1283, dated April 3, 2007. Doing
this installation ends the requirements of
paragraphs (f) and (g) of this AD. Any flight
spoiler actuator with P/N P665A0001–01 (or
higher dash number) that was previously
installed in any flight spoiler position in
accordance with the requirements of AD
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2007–06–52 is acceptable for meeting the
requirements of this AD for that flight spoiler
position.
Parts Installation
(i) As of May 7, 2007, no person may
install a flight spoiler actuator, having P/N
P665A0001–00, on any airplane.
Parts Return
(j) Although the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–27A1283, dated April 3, 2007, describe
procedures for returning parts to the vendor,
this AD does not require that action.
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 subject to the requirements
of paragraphs (k)(1) and (k)(2) of this AD.
(1) Special flight permits are not allowed
if any flight spoiler is found in the up
position during any visual check required by
paragraph (f) of this AD.
(2) Special flight permits are allowed for
ferry flights to a maintenance location to
accomplish the flight spoiler actuator
installation required by paragraph (h) of this
AD if no flight spoiler has failed any visual
check required by paragraph (f) of this AD.
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.
(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) AMOCs approved previously in
accordance with AD 2007–06–52 are
approved as AMOCs for the corresponding
provisions of this AD.
Material Incorporated by Reference
(m) You must use Boeing 737 Flight Crew
Operations Manual Bulletin No. TBC–67,
dated March 5, 2007; and Boeing Alert
Service Bulletin 737–27A1283, dated April 3,
2007; as applicable, to perform the actions
that are required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 737–27A1283,
dated April 3, 2007, in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) On May 7, 2007 (72 FR 21083, April 30,
2007), the Director of the Federal Register
approved the incorporation by reference of
Boeing 737 Flight Crew Operations Manual
Bulletin No. TBC–67, dated March 5, 2007.
(3) 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
E:\FR\FM\24JYR1.SGM
24JYR1
40230
Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations
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/ibrlocations.html.
Issued in Renton, Washington, on July 11,
2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–13979 Filed 7–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28747; Directorate
Identifier 2006–NM–275–AD; Amendment
39–15137; AD 2007–15–08]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited Model
ATP Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
pwalker on PROD1PC71 with RULES
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to all BAE Systems
(Operations) Limited Model ATP
airplanes. The existing AD currently
requires revising the Airworthiness
Limitations Section (ALS) of the
Instructions for Continued
Airworthiness (ICA) to incorporate life
limits for certain items and inspections
to detect fatigue cracking in certain
structures; to incorporate new
inspections to detect fatigue cracking of
certain significant structural items
(SSIs); and to revise life limits for
certain equipment and various
components. This new AD requires
revising the ALS of the ICA to include
revised requirements. This AD results
from the determination that additional
and revised inspections of the fuselage
are needed. We are issuing this AD to
detect and correct fatigue cracking of
certain structural elements, which could
result in reduced structural integrity of
the airplane and consequent rapid
decompression of the airplane.
DATES: This AD becomes effective
August 8, 2007.
On September 21, 2006 (71 FR 52418,
September 6, 2006), the Director of the
Federal Register approved the
incorporation by reference of BAE
VerDate Aug<31>2005
17:17 Jul 23, 2007
Jkt 211001
Systems (Operations) Limited Service
Bulletin ATP–51–002, dated December
20, 2005.
We must receive comments on this
AD by September 24, 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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact British Aerospace Regional
Aircraft American Support, 13850
Mclearen Road, Herndon, Virginia
20171, for service information identified
in this AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
On August 23, 2006, we issued AD
2006–18–09, amendment 39–14748 (71
FR 52418, September 6, 2006), for all
BAE Systems (Operations) Limited
Model ATP airplanes. That AD requires
revising the Airworthiness Limitations
Section (ALS) of the Instructions for
Continued Airworthiness (ICA) to
incorporate life limits for certain items
and inspections to detect fatigue
cracking in certain structures; to
incorporate new inspections to detect
fatigue cracking of certain significant
structural items (SSIs); and to revise life
limits for certain equipment and various
components. That AD resulted from
manufacturer review of fatigue test
results that identified additional and
revised inspections of the fuselage that
are necessary in order to ensure the
continued structural integrity of the
airplane. We issued that AD to detect
and correct fatigue cracking of certain
structural elements, which could result
in reduced structural integrity of the
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
airplane and consequent rapid
decompression of the airplane. The
actions specified in that AD correspond
to British airworthiness directive G–
2004–0020, dated August 25, 2004, and
European Aviation Safety Agency
(EASA) airworthiness directive 2006–
0090, dated April 20, 2006.
Actions Since Existing AD Was Issued
Since we issued AD 2006–18–09, the
Civil Aviation Authority (CAA), which
is the airworthiness authority for the
United Kingdom, notified us that an
unsafe condition may exist on all BAE
Systems (Operations) Limited Model
ATP airplanes. The CAA advises that
the certification requirements for
damage tolerant and safe life structure
are given in Chapter 5 of the BAE ATP
aircraft maintenance manual (AMM).
The CAA has identified the need to
revise these requirements to add and
change inspections of the fuselage. The
revisions primarily recognize the
introduction of Modification
JDM60138N, which installs an energyabsorbing stop to aircraft fitted with the
large freight door. Failure to adopt the
latest revision of Chapter 5 of the AMM
could result in fatigue cracking of
certain structural elements remaining
undetected, which could result in
reduced structural integrity of the
airplane and consequent rapid
decompression of the airplane.
Relevant Service Information
BAE Systems (Operations) Limited
has issued revisions to Section 05–10–
12, ‘‘Mandatory Life Limitations
(Airframe—Structures),’’ dated January
15, 2007; Section 05–10–15,
‘‘Mandatory Life Limitations
(Powerplant/Engine/APU—Structures),’’
dated January 15, 2007; and Section 05–
10–17, ‘‘Structurally Significant Items
(SSIs),’’ dated January 15, 2007; of the
BAE Systems (Operations) Limited ATP
AMM; which refer to additional
chapters of the AMM. Those revised
sections of the AMM include mandatory
life limitations for the airframe and
power plant/engine; and structural
inspections of the fuselage, engine,
horizontal stabilizer, and wing bottom
surface. The revised sections also
describe new inspections and
compliance times for inspection and
replacement actions. Accomplishment
of those actions will prevent the onset
of fatigue cracking of certain structural
elements of the airplane.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. The CAA mandated the
service information and issued British
airworthiness directive G–2005–0031,
E:\FR\FM\24JYR1.SGM
24JYR1
]]>Agencies
[Federal Register Volume 72, Number 141 (Tuesday, July 24, 2007)]
[Rules and Regulations]
[Pages 40226-40230]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13979]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28750; Directorate Identifier 2007-NM-124-AD;
Amendment 39-15133; AD 2007-15-04]
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.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to certain Boeing Model 737-800 series airplanes. The
existing AD currently requires inspecting flight spoilers to determine
spoiler position after every landing and after any rejected takeoff
maneuver. For airplanes on which any flight spoiler is found in the up
position with the speedbrake handle in the down position, the existing
AD requires replacing the flight spoiler actuator with a flight spoiler
actuator having a certain part number. The existing AD also requires an
operational test of the speedbrake
[[Page 40227]]
control system after any maintenance actions that operate the spoiler
system, and replacement of the flight spoiler actuator if necessary.
The existing AD also provides for optional terminating action for those
requirements. This new AD requires the previously optional terminating
action. This AD results from a report of seven flight spoiler actuator
jams on Model 737-800 airplanes equipped for short field performance
(SFP). The cause of the failure has been identified as interference
within the actuator main control valve. We are issuing this AD to
prevent operation with defective flight spoiler actuators, which could
result in a flight spoiler actuator hardover, and could cause the
flight spoiler surface to jam in the fully extended position. Two or
more hardover failures of the flight 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 August 8, 2007.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of August 8,
2007.
On May 7, 2007 (72 FR 21083, April 30, 2007), the Director of the
Federal Register approved the incorporation by reference of a certain
publication listed in the AD.
We must receive any comments on this AD by September 24, 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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., 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:
Discussion
On April 18, 2007, we issued AD 2007-06-52, amendment 39-15036 (72
FR 21083, April 30, 2007). That AD applies to certain Boeing Model 737-
800 series airplanes. That AD requires inspecting flight spoilers to
determine spoiler position after every landing and after any rejected
takeoff maneuver. For airplanes on which any flight 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(s) 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.
The actions specified in that AD are intended 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.
The goal of the actions required by AD 2007-06-52 is to detect
actuators that might have failed during the previous flight in order to
prevent an attempted takeoff with extended flight spoiler(s). We
determined that takeoff is the most critical portion of the flight
profile for this particular failure, but it is not the only flight
profile that could be affected. Therefore, we are issuing this new AD
for the following reasons:
Replacing all flight spoiler actuators is the best method
to eliminate the possibility of this failure.
The inspections and operational tests required by AD 2007-
06-52 are an interim solution and cannot detect or prevent other
possible scenarios involving a failed flight spoiler actuator.
Inspecting each flight spoiler after every landing and
after any rejected takeoff maneuver does not guarantee that the flight
spoiler will function properly during the next flight.
Actions Since AD Was Issued
The preamble to AD 2007-06-52 explains that we consider the
requirements ``interim action'' and are considering requiring the
replacement of all eight flight spoiler actuators. We now have
determined that replacement of the flight spoiler actuators is
necessary, and this AD follows from that determination. The replacement
actuators correct the interference condition in the valve assembly,
eliminate possible rate jam conditions, and ensure continued correct
operation of the flight spoilers. Replacement of all flight spoiler
actuators constitutes terminating action for the requirements of AD
2007-06-52.
In addition, paragraph (g) of AD 2007-06-52 also specifies that the
Master Minimum Equipment List (MMEL) Item 27-7, ``Auto Speed Brake
System,'' is no longer applicable to Model 737-800 series airplanes
equipped with an SFP package. Since we issued AD 2007-06-52, Boeing has
revised MMEL Item 27-7 to accurately reflect the operational
requirements to account for the degraded performance when operating a
Model 737-800 series airplane equipped with the SFP package when it has
the auto speed brake system disabled. Therefore, the requirement in
paragraph (g) of AD 2007-06-52 has not been restated in this AD. We
have re-lettered the remaining paragraphs accordingly.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-27A1283, dated
April 3, 2007. The service bulletin describes procedures for installing
an improved SFP actuator for each of the eight flight spoilers. The
installation includes replacing the SFP actuator, making sure there is
no hydraulic leakage at the connections to each of the new, improved
SFP actuators, and completing all adjustments and tests of each flight
spoiler to make sure it operates correctly. The service bulletin
specifies doing the adjustments and tests in accordance with the
applicable aircraft maintenance manual. The service bulletin also
specifies returning each removed flight spoiler SFP actuator to the
vendor for modification. The service bulletin includes eight individual
work packages for replacement of each of the eight flight spoiler
actuators to allow flexibility in accomplishing the service bulletin.
[[Page 40228]]
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design. For this reason, we
are issuing this AD to supersede AD 2007-06-52. This new AD retains
certain requirements of the existing AD. This AD also requires
accomplishing the actions specified in the service bulletin described
previously, except as discussed under ``Difference Between the AD and
the Service Bulletin.'' This AD allows 120 days from its effective date
to accomplish the required actions. This amount of time is necessary to
enable operators to obtain sufficient parts to modify all affected
airplanes.
Difference Between the AD and the Service Bulletin
Operators should note that, although the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-27A1283, dated April
3, 2007, describe procedures for returning parts to the vendor, this AD
does not require that action.
Change to Alternative Methods of Compliance (AMOCs) Paragraph
AD 2007-06-52 requires accomplishing certain actions in accordance
with Boeing 737 Flight Crew Operations Manual Bulletin No. TBC-67,
dated March 5, 2007. That document is specific to Boeing operations.
Since we issued AD 2007-06-52, Boeing has released operator-specific
versions of Bulletin No. TBC-67 for affected operators of Model 737-800
airplanes equipped with the SFP package. The operator-specific
documents have been approved as AMOCs for AD 2007-06-52. For
simplicity, paragraph (f)(1) of this new AD continues to require
actions in accordance with Bulletin No. TBC-67. However, paragraph
(l)(3) has been added to this AD to specify that the existing AMOCs
that approve operator-specific documents continue to be acceptable.
Clarification of Terminology
We use the term ``flight spoilers,'' ``flight spoiler actuators,''
or ``SFP actuators,'' in this AD to refer to the affected spoilers and
actuators. There are ground spoilers on the affected airplanes, but the
ground spoilers have a different type of actuator and are not affected
by this AD. We have added Note 1 to this AD to include this
clarification.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
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-
28750; Directorate Identifier 2007-NM-124-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 Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The
Docket Operations office (telephone (800) 647-5527) is located on the
ground floor of the West Building at the 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 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.
For the reasons discussed above, I certify that the 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 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends part 39 of the Federal Aviation Regulations (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 Federal Aviation Administration (FAA) amends Sec. 39.13
[[Page 40229]]
by removing amendment 39-15036 (72 FR 21083, April 30, 2007) and adding
the following new airworthiness directive (AD):
2007-15-04 Boeing: Docket No. FAA-2007-28750; Directorate Identifier
2007-NM-124-AD; Amendment 39-15133.
Effective Date
(a) This AD becomes effective August 8, 2007.
Affected ADs
(b) This AD supersedes AD 2007-06-52.
Applicability
(c) This AD applies to 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 series airplanes equipped for short
field performance (SFP). The cause of the failure has been
identified as interference within the actuator main control valve.
We are issuing this AD to prevent operation with defective flight
spoiler actuators, 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 flight
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.
Note 1: We use the term ``flight spoilers,'' ``flight spoiler
actuators,'' or ``SFP actuators,'' in this AD to refer to the
affected spoilers and actuators. There are ground spoilers on the
affected airplanes, but the ground spoilers have a different type of
actuator and are not affected by this AD.
Restatement of the Requirements of AD 2007-06-52
Visual Check and Corrective Action
(f) Within 24 clock hours after May 7, 2007 (the effective date
of AD 2007-06-52), do the actions specified in paragraphs (f)(1),
(f)(2), and (f)(3) of this AD, as applicable, until the action
required by paragraph (h) of this AD is accomplished. 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.
Reporting
(g) If any spoiler is found to be improperly stowed during any
visual check required by this AD, at the applicable time specified
in paragraphs (g)(1) and (g)(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.
Doing the action required by paragraph (h) of this AD terminates the
requirements of this paragraph.
(1) For visual checks done before May 7, 2007: Within 7 days
after May 7, 2007.
(2) For visual checks done after May 7, 2007: Within 7 days
after doing the inspection.
New Requirements of This AD
Terminating Action
(h) Within 120 days after the effective date of this AD: Install
flight spoiler actuator, P/N P665A0001-01 or higher dash number, in
all eight flight spoiler positions in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
27A1283, dated April 3, 2007. Doing this installation ends the
requirements of paragraphs (f) and (g) of this AD. Any flight
spoiler actuator with P/N P665A0001-01 (or higher dash number) that
was previously installed in any flight spoiler position in
accordance with the requirements of AD 2007-06-52 is acceptable for
meeting the requirements of this AD for that flight spoiler
position.
Parts Installation
(i) As of May 7, 2007, no person may install a flight spoiler
actuator, having P/N P665A0001-00, on any airplane.
Parts Return
(j) Although the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-27A1283, dated April 3, 2007, describe
procedures for returning parts to the vendor, this AD does not
require that action.
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 subject to the requirements of paragraphs (k)(1)
and (k)(2) of this AD.
(1) Special flight permits are not allowed if any flight spoiler
is found in the up position during any visual check required by
paragraph (f) of this AD.
(2) Special flight permits are allowed for ferry flights to a
maintenance location to accomplish the flight spoiler actuator
installation required by paragraph (h) of this AD if no flight
spoiler has failed any visual check required by paragraph (f) of
this AD.
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.
(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) AMOCs approved previously in accordance with AD 2007-06-52
are approved as AMOCs for the corresponding provisions of this AD.
Material Incorporated by Reference
(m) You must use Boeing 737 Flight Crew Operations Manual
Bulletin No. TBC-67, dated March 5, 2007; and Boeing Alert Service
Bulletin 737-27A1283, dated April 3, 2007; as applicable, to perform
the actions that are required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Alert Service Bulletin 737-
27A1283, dated April 3, 2007, in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
(2) On May 7, 2007 (72 FR 21083, April 30, 2007), the Director
of the Federal Register approved the incorporation by reference of
Boeing 737 Flight Crew Operations Manual Bulletin No. TBC-67, dated
March 5, 2007.
(3) 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
[[Page 40230]]
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 July 11, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-13979 Filed 7-23-07; 8:45 am]
BILLING CODE 4910-13-P
