Airworthiness Directives; Boeing Model 737-300, -400, -500, -600, -700, -700C, -800, and -900, and 747-400 Series Airplanes; and Model 757, 767, and 777 Airplanes, 68501-68505 [E9-29963]
Download as PDF
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Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations
erowe on DSK5CLS3C1PROD with RULES
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
This Airworthiness Directive (AD) is
prompted due to the discovery of cracks
caused by stress corrosion in the main-gear
support struts. All the main-gear support
struts that had cracks were made from
material AA2024–T351 which has a lower
resistance to stress corrosion cracking.
Such cracks, if undetected, could lead to
the failure of the strut during landing which
could then cause the Main Landing Gear
(MLG) to collapse.
In order to correct and control the
situation, this AD mandates the identification
of the main-gear support struts to check if
they have rounded clevis lugs and a NonDestructive Inspection (NDI) procedure on
the main-gear support struts if they have
chamfered clevis lugs.
For main-gear support struts with chamfered
clevis lugs that show cracks during the NDI,
the MCAI also requires replacing any cracked
main-gear support struts with parts of
improved design. You may obtain further
information by examining the MCAI in the
AD docket.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) Within the next 30 hours time-inservice (TIS) after February 1, 2010 (the
effective date of this AD) or within the next
30 days after February 1, 2010 (the effective
date of this AD), whichever occurs first,
visually inspect the left and right main-gear
support struts to determine if they have
rounded or chamfered clevis lugs. Do the
inspection following paragraph 3.A. of
Pilatus PC–7 Service Bulletin No. 32–024,
Rev. No. 1, dated November 17, 2008.
(2) Based on the results of the inspection
required in paragraph (f)(1) of this AD, if the
main-gear support strut has rounded clevis
lugs, no further action is required except the
requirement specified in paragraph (f)(4) of
this AD still applies. Make an entry in the
airplane logbook to show compliance with
this AD. Based on the reports of the results
of the inspection required by this AD, further
rulemaking action may be taken to mandate
repetitive inspections or terminating action.
(3) Based on the results of the inspection
required in paragraph (f)(1) of this AD, if the
main-gear support strut has chamfered clevis
lugs, before further flight do a NonDestructive Inspection (NDI). Do the NDI
following paragraphs 3.B. through 3.E. of
Pilatus PC–7 Service Bulletin No. 32–024,
Rev. No. 1, dated November 17, 2008.
(i) If cracks are found during the inspection
required in paragraph (f)(3) of this AD:
(A) Before further flight after the
inspection, replace any cracked main-gear
support struts with new main-gear support
struts, P/N 532.10.09.128. Do the
replacement following Pilatus PC–7 Service
Bulletin No. 32–025, Rev. No. 1, dated
November 17, 2008.
(B) Within the next 10 days after the
inspection, report the cracks to Pilatus
Aircraft LTD., Customer Liaison Manager,
CH–6371 STANS, Switzerland, using the
Crack Report Form (Figure 4) in Pilatus PC–
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7 Service Bulletin No. 32–024, Rev. No. 1,
dated November 17, 2008.
(ii) If no cracks are found during the
inspection required in paragraph (f)(3) of this
AD, no further action is required. Make an
entry in the airplane logbook to show
compliance with this AD.
(4) As of 30 days after February 1, 2010
(the effective date of this AD), do not install
any main-gear support struts, P/N
532.10.09.039 or P/N 114.48.07.127, with
chamfered clevis lugs.
Note 1: If you have any main-gear support
struts, P/N 532.10.09.039 or P/N
114.48.07.127, with chamfered clevis lugs
held as spares, you may return them to
Pilatus Aircraft Ltd., Customer Liaison
Manager, CH–6371 STANS, Switzerland, for
replacement with a new main-gear support
strut, P/N 532.10.09.128.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
Attn: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; fax: (816) 329–
4090; e-mail: doug.rudolph@faa.gov. 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.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI Federal Office of Civil
Aviation AD HB–2009–011, dated September
10, 2009; and Pilatus PC–7 Service Bulletin
No. 32–024, Rev. No. 1, dated November 17,
2008; and Pilatus PC–7 Service Bulletin No.
32–025, Rev. No. 1, dated November 17,
2008, for related information.
Material Incorporated by Reference
(i) You must use Pilatus PC–7 Service
Bulletin No. 32–024, Rev. No. 1, dated
November 17, 2008; and Pilatus PC–7 Service
Bulletin No. 32–025, Rev. No. 1, dated
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68501
November 17, 2008, to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Pilatus Aircraft LTD.,
Customer Service Manager, CH–6371
STANS, Switzerland; telephone: +41 (0)41
619 62 08; fax: +41 (0)41 619 73 11; Internet:
https://www.pilatus-aircraft.com/, or e-mail:
snolan@pilatus-aircraft.com.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
for this AD 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Kansas City, MO, on December 8,
2009.
Margaret Kline,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–29983 Filed 12–24–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0911; Directorate
Identifier 2002–NM–12–AD; Amendment 39–
16138; AD 2009–26–03]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–300, –400, –500, –600, –700,
–700C, –800, and –900, and 747–400
Series Airplanes; and Model 757, 767,
and 777 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 737–300, –400, –500,
–600, –700, –700C, –800, and –900, and
747–400 series airplanes; and Model
757, 767, and 777 airplanes. This AD
requires modifying the static inverter by
replacing resistor R170 with a new
resistor and relocating the new resistor.
This AD results from evaluation of the
carbon resistor, which revealed a failure
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Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations
mode that can cause the resistor to
ignite, involving adjacent capacitors as
well. We are issuing this AD to prevent
a standby static inverter from
overheating, which could result in
smoke in the flight deck and cabin and
loss of the electrical standby power
system.
DATES: This AD becomes effective
February 1, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of February 1, 2010.
For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P. O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1, fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
ADDRESSES:
Examining the AD Docket
SUPPLEMENTARY INFORMATION:
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Binh V. Tran, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6485; fax (425) 917–6590.
Discussion
The FAA issued a second
supplemental notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Boeing Model 737–300,
–400, –500, –600, –700, –700C, –800,
and –900, and 747–400 series airplanes;
and Model 757, 767, and 777 airplanes.
That second supplemental NPRM was
published in the Federal Register on
January 12, 2009 (74 FR 1159). That
second supplemental NPRM proposed
to require modifying the static inverter
by replacing resistor R170 with a new
resistor and relocating the new resistor.
Actions Since Issuance of Second
Supplemental NPRM
Since issuance of the second
supplemental NPRM, Boeing has issued
the revised service bulletins listed in the
following table:
REVISED SERVICE BULLETINS
Model—
Boeing—
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737–300, –400, –500 series airplanes ...............
757–200, –200CB, –200PF series airplanes .....
757–300 series airplanes ...................................
No additional work is necessary for
airplanes on which the modification
specified in Boeing Alert Service
Bulletin 737–24A1166, Revision 3,
dated July 25, 2007, has been done.
Revision 4 clarifies certain sections,
moves airplanes from Group 2 to Group
1 in the effectivity, and removes the
Group 2 work instructions.
Boeing Special Attention Service
Bulletin 757–24–0110, Revision 1, dated
August 6, 2009, adds an inspection of
certain static inverter part numbers to
make sure only approved part numbers
are installed; however, the proposed
modification requires modifying the
static inverter by replacing the resistor
with a new resistor having an approved
part number. Revision 1 also moves
airplanes from Group 2 to Group 1 in
the effectivity, and the Group 2 work
instructions were deleted. Therefore, no
additional work is necessary for
airplanes modified in accordance with
Boeing Special Attention Service
Bulletin 757–24–0110, dated April 28,
2005.
Boeing Special Attention Service
Bulletin 757–24–0111, Revision 1, dated
August 6, 2009, also adds an inspection
of certain static inverter part numbers to
make sure only approved part numbers
are installed; however, the proposed
modification requires modifying the
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Alert Service Bulletin 737–24A1166, Revision 4, dated May 21, 2009.
Special Attention Service Bulletin 757–24–0110, Revision 1, dated August 6, 2009.
Special Attention Service Bulletin 757–24–0111, Revision 1, dated August 6, 2009.
static inverter by replacing the resistor
with a new resistor having an approved
part number. Revision 1 also moves
airplanes from Group 2 to Group 1 in
the effectivity, and the Group 2 work
instructions were deleted. No additional
work is necessary for airplanes modified
in accordance with Boeing Special
Attention Service Bulletin 757–24–
0111, dated April 28, 2005.
We have revised Table 1 of this AD
to refer to the latest revisions of the
service bulletins and added a new
paragraph (h) to this AD to give credit
for actions done in accordance with the
earlier revisions that were referenced in
Table 1 of the NPRM.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received on
the second supplemental NPRM.
Support for the Second Supplemental
NPRM
Northwest Airlines has no objection
to the second supplemental NPRM;
Boeing concurs with the content of the
second supplemental NPRM.
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Request To Permit Installation of Static
Inverters Having Certain Part Numbers
American Airlines (AAL) and FedEx
Express request that we allow
installation of static inverters having
certain part numbers.
AAL asks that we permit installation
of static inverters having part numbers
(P/Ns) S282T004–2, –3, and –4. AAL
states that those static inverters do not
have an overheating safety concern,
which is the unsafe condition addressed
in the second supplemental NPRM.
AAL adds that static inverters that have
P/Ns S282T004–2, –3, and –4 are fully
interchangeable on the Model 757 fleet.
FedEx Express asks that Boeing
Special Attention Service Bulletin 757–
24–0110, dated April 28, 2005, be
revised to include Avionics Instruments
static inverters having P/Ns S282T004–
28 and S282T004–30 as acceptable to
remain on Model 757 airplanes. FedEx
Express adds that since issuance of the
original issue of Boeing Special
Attention Service Bulletin 757–24–
0110, those static inverters have been
installed on some Model 757 airplanes
and have been added to the Boeing
Illustrated Parts Catalog. FedEx Express
notes that P/Ns S282T004–2, –3, –4,
–28, and –30 should be the P/Ns for the
static inverters installed in accordance
with the requirements in the second
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Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations
supplemental NPRM. FedEx Express
adds that combining Groups 1 and 2
into one group would accomplish this
task.
We agree with the commenters’
requests and provide the following
explanation. As noted previously,
Boeing has issued Special Attention
Service Bulletin 757–24–0110, Revision
1, dated August 6, 2009. The effectivity
specified in Revision 1 is changed to
move airplanes from Group 2 to Group
1, and to remove the Group 2 work
instructions by combining Group 2 work
instructions with Group 1. The work
instructions specified in Revision 1 also
add an inspection for certain static
inverter part numbers that allows for
installation of static inverters having
P/Ns S282T004–2, –3, –4, –25, –28, and
–30. Inspection of the static inverter
P/Ns will prevent unnecessary
replacement of approved static
inverters. We have changed the
applicability in paragraph (c) of this AD
to identify Revision 1 of Boeing Special
Attention Service Bulletin 757–24–
0110.
Request To Include Revised Service
Information
AAL states that it found a discrepancy
in Figure 1 of Boeing Special Attention
Service Bulletin 767–24–0160, dated
June 30, 2005 (referred to in the second
supplemental NPRM), and asks that this
service bulletin be revised to correct the
discrepancy. AAL adds that the
discrepancy is in Figure 1, which
specifies an inspection of the static
inverter on Groups 1 and 3 airplanes.
Figure 2 also contains an error which
specifies the actions are applicable to
Group 3 airplanes. However, Group 2
airplanes are not identified in either of
these figures. AAL also notes that in
Boeing Service Message 1–1156909141–
2, Boeing specifies that static inverters
having P/Ns S282T004–2, –3, –4 are
acceptable for installation across the
Model 757 airplane fleet since the
Model 767 airplane fleet uses the same
static inverter.
We acknowledge the commenter’s
concern and agree that the error in
Figure 1 of Boeing Special Attention
Service Bulletin 767–24–0160, dated
June 30, 2005, should be corrected in a
revision; but we do not consider that
delaying the final rule until after the
release of a future revision is warranted.
The original issue of Boeing Special
Attention Service Bulletin 767–24–0160
includes sufficient information to
accomplish the modification of the
static inverter. However, we have added
new paragraph (g) to this AD to exclude
Group 2 airplanes that have a static
inverter with part number S282T004–2,
S282T004–3, or S282T004–4, from the
modification requirement. We have reidentified subsequent paragraphs
accordingly.
Request To Change Cost Impact Section
AAL states that the cost estimate for
material and labor necessary for
accomplishing the modification on its
airplanes is more than the estimate in
the second supplemental NPRM.
We infer that AAL is asking that the
work hours and cost specified in the
Cost Impact section of the AD be
increased. We do not agree. The cost
information below describes only the
direct costs of the specific actions
required by this AD. Based on the best
data available, the manufacturer
provided the number of work hours (up
to 2 hours, depending on airplane
configuration) necessary to do the
required actions. This number
represents the time necessary to perform
only the actions actually required by
this AD. We recognize that, in doing the
actions required by an AD, operators
might incur incidental costs in addition
to the direct costs. The cost analysis in
AD rulemaking actions, however,
typically does not include incidental
costs such as the time required to gain
access and close up, time necessary for
planning, or time necessitated by other
administrative actions. Those incidental
costs, which might vary significantly
among operators, are almost impossible
to calculate. We have not changed the
AD in this regard.
68503
Request for Clarification
Cargolux Airlines International S.A.
states that it has followed the history of
the proposed rule since 2003, and is not
aware of any new event reported on the
static inverters since that time. Cargolux
asks for clarification that only one
airplane was affected prior to 2003, and
no airplanes were affected after 2003.
Cargolux also asks for the number of
occurrences of R170 resistors
overheating, and the number of units
manufactured.
We acknowledge the commenter’s
request and provide the following
clarification. Prior to 2003 there were 39
static inverter failures on 39 airplanes;
since 2003 there have been 15 inverters
on 15 airplanes that failed due to the
R170 resistor overheating, and
approximately 9,400 units have been
manufactured.
Explanation of Additional Paragraph in
the Final Rule
We have added a new paragraph (d)
to this AD to provide the Air Transport
Association (ATA) of America code 24:
Electrical power. This code is added to
make this AD parallel with other new
AD actions. We have reidentified
subsequent paragraphs accordingly.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
There are approximately 3,856
airplanes of the affected design in the
worldwide fleet. The FAA estimates that
1,882 airplanes of U.S. registry will be
affected by this AD. The following table
provides the estimated costs for U.S.
operators to comply with this AD.
ESTIMATED COSTS
Work hours
Average labor
rate per hour
Parts
Modification .....
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Action
Up to 2 hours, depending on
airplane configuration.
$80
$0
The cost impact figure discussed
above is based on assumptions that no
operator has yet accomplished any of
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10:44 Dec 24, 2009
Jkt 220001
Cost per airplane
Between $80
and $160.
the proposed requirements of this AD
action, and that no operator would
accomplish those actions in the future if
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Number of
U.S.-registered
airplanes
1,882
Fleet cost
Up to $301,120.
the AD were not adopted. The cost
impact figures discussed in AD
rulemaking actions represent only the
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Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations
Regulatory Findings
time necessary to perform the specific
actions actually required by the AD.
These figures typically do not include
incidental costs, such as the time
required to gain access and close up,
planning time, or time necessitated by
other administrative 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
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.
Adoption of the Amendment
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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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
Applicability
(c) This AD applies to the following
airplanes, certificated in any category, as
identified in the applicable Boeing service
bulletin specified in Table 1 of this AD:
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
■
2009–26–03 Boeing: Amendment 39–16138.
Docket No. FAA–2009–0911; Directorate
Identifier 2002–NM–12–AD.
Effective Date
(a) This AD becomes effective February 1,
2010.
Affected ADs
(b) None.
TABLE 1—APPLICABILITY
Model—
Boeing—
737–600, –700, –700C, –800, –900 series airplanes.
737–300, –400, –500 series airplanes ...............
747–400, –400D, –400F series airplanes ..........
757–200, –200CB, –200PF series airplanes .....
757–300 series airplanes ...................................
767–200, –300, –300F series airplanes .............
767–400ER series airplanes ..............................
777–200, –300, –300ER series airplanes ..........
Special Attention Service Bulletin 737–24–1165, Revision 1, dated October 20, 2005.
Alert Service Bulletin 737–24A1166, Revision 4, dated May 21, 2009.
Service Bulletin 747–24–2254, Revision 1, dated March 5, 2007.
Special Attention Service Bulletin 757–24–0110, Revision 1, dated August 6, 2009.
Special Attention Service Bulletin 757–24–0111, Revision 1, dated August 6, 2009.
Special Attention Service Bulletin 767–24–0160, dated June 30, 2005.
Special Attention Service Bulletin 767–24–0161, dated June 30, 2005.
Service Bulletin 777–24–0095, Revision 1, dated January 3, 2007.
Subject
Modification
(d) Air Transport Association (ATA) of
America Code 24: Electrical power.
(f) At the time specified in paragraph (f)(1)
or (f)(2) of this AD, as applicable: Modify the
static inverter by removing resistor R170
from the logic control card assembly and
replacing it with a new resistor, and
relocating the new resistor to the solder side
of the printed circuit board, in accordance
with the Accomplishment Instructions of the
applicable service bulletin specified in Table
1 of this AD, except as provided by paragraph
(g) of this AD.
(1) For Model 737, 757, and 767 airplanes:
Within 42 months after the effective date of
this AD.
Unsafe Condition
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(e) This AD results from evaluation of the
carbon resistor, which revealed a failure
mode that can cause the resistor to ignite,
involving adjacent capacitors as well. The
Federal Aviation Administration is issuing
this AD to prevent a standby static inverter
from overheating, which could result in
smoke in the flight deck and cabin and loss
of the electrical standby power system.
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10:44 Dec 24, 2009
Jkt 220001
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(2) For Model 747 and 777 airplanes:
Within 60 months after the effective date of
this AD.
(g) For Group 2 airplanes identified Boeing
Special Attention Service Bulletin 767–24–
0160, dated June 30, 2005: Airplanes having
a static inverter with part number S282T004–
2, S282T004–3, or S282T004–4, are not
required to do the modification specified in
paragraph (f) of this AD.
(h) Actions accomplished before the
effective date of this AD in accordance with
the applicable Boeing service bulletin
specified in Table 2 of this AD, are
considered acceptable for compliance with
the corresponding actions specified in this
AD.
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Federal Register / Vol. 74, No. 247 / Monday, December 28, 2009 / Rules and Regulations
68505
TABLE 2—PREVIOUSLY ISSUED SERVICE INFORMATION
Boeing —
Revision—
Dated—
Alert Service Bulletin 737–24A1166 .........................................................................................................
Special Attention Service Bulletin 757–24–0110 .....................................................................................
Special Attention Service Bulletin 757–24–0111 .....................................................................................
3 .......................
Original .............
Original .............
July 25, 2007.
April 28, 2005.
April 28, 2005.
Note 1: The Boeing service bulletins
specified in Table 1 of this AD refer to
Avionic Instruments Inc. Service Bulletins 1–
002–0102–1000–24–28, Revision A, dated
June 22, 2005; and Revision B, dated July 24,
2006; as additional sources of guidance for
accomplishing the modification required by
paragraph (f) of this AD.
Alternative Methods of Compliance
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Binh
V. Tran, Aerospace Engineer, Systems and
Equipment Branch, ANM–130S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6485; fax (425)
917–6590. Or, e-mail information to 9–ANM–
Seattle-ACO–AMOC–Requests@faa.gov.
(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 principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
Material Incorporated by Reference
(j) You must use the applicable Boeing
service information contained in Table 3 of
this AD to do the actions required by this AD,
unless the AD specifies otherwise.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE
Boeing—
Revision—
Dated—
Alert Service Bulletin 737–24A1166 .........................................................................................................
Service Bulletin 747–24–2254 ..................................................................................................................
Service Bulletin 777–24–0095 ..................................................................................................................
Special Attention Service Bulletin 737–24–1165 .....................................................................................
Special Attention Service Bulletin 757–24–0110 .....................................................................................
Special Attention Service Bulletin 757–24–0111 .....................................................................................
Special Attention Service Bulletin 767–24–0160 .....................................................................................
Special Attention Service Bulletin 767–24–0161 .....................................................................................
4 .......................
1 .......................
1 .......................
1 .......................
1 .......................
1 .......................
Original .............
Original .............
May 21, 2009.
March 5, 2007.
January 3, 2007.
October 20, 2005.
August 6, 2009.
August 6, 2009.
June 30, 2005.
June 30, 2005.
erowe on DSK5CLS3C1PROD with RULES
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1, fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference 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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
December 4, 2009.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–29963 Filed 12–24–09; 8:45 am]
BILLING CODE 4910–13–P
VerDate Nov<24>2008
10:44 Dec 24, 2009
Jkt 220001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1209; Directorate
Identifier 2009–NM–151–AD; Amendment
39–16147; AD 2008–04–11 R1]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 707 Airplanes, and
Model 720 and 720B Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: The FAA is revising an
existing airworthiness directive (AD),
which applies to all Model 707
airplanes, and Model 720 and 720B
series airplanes. That AD currently
requires revising the FAA-approved
maintenance program by incorporating
new airworthiness limitations (AWLs)
for fuel tank systems to satisfy Special
Federal Aviation Regulation No. 88
requirements. That AD also requires an
initial inspection to phase in certain
repetitive AWL inspections, and repair
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
if necessary. This AD clarifies the
intended effect of the AD on spare and
on-airplane fuel tank system
components. This AD results from
design review of the fuel tank systems.
We are issuing this AD to prevent the
potential for ignition sources inside fuel
tanks caused by latent failures,
alterations, repairs, or maintenance
actions, which, in combination with
flammable fuel vapors, could result in
fuel tank explosions and consequent
loss of the airplane.
DATES: This AD is effective January 12,
2010.
On March 28, 2008 (73 FR 9666,
February 22, 2008), 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 February 11, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
E:\FR\FM\28DER1.SGM
28DER1
]]>Agencies
[Federal Register Volume 74, Number 247 (Monday, December 28, 2009)]
[Rules and Regulations]
[Pages 68501-68505]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-29963]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0911; Directorate Identifier 2002-NM-12-AD;
Amendment 39-16138; AD 2009-26-03]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-300, -400, -500, -600,
-700, -700C, -800, and -900, and 747-400 Series Airplanes; and Model
757, 767, and 777 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 737-300, -400, -500, -600, -700, -700C, -800, and
-900, and 747-400 series airplanes; and Model 757, 767, and 777
airplanes. This AD requires modifying the static inverter by replacing
resistor R170 with a new resistor and relocating the new resistor. This
AD results from evaluation of the carbon resistor, which revealed a
failure
[[Page 68502]]
mode that can cause the resistor to ignite, involving adjacent
capacitors as well. We are issuing this AD to prevent a standby static
inverter from overheating, which could result in smoke in the flight
deck and cabin and loss of the electrical standby power system.
DATES: This AD becomes effective February 1, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of February 1,
2010.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management, P.
O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1, fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Binh V. Tran, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6485; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a second supplemental notice of proposed rulemaking
(NPRM) to amend 14 CFR part 39 to include an AD that would apply to
certain Boeing Model 737-300, -400, -500, -600, -700, -700C, -800, and
-900, and 747-400 series airplanes; and Model 757, 767, and 777
airplanes. That second supplemental NPRM was published in the Federal
Register on January 12, 2009 (74 FR 1159). That second supplemental
NPRM proposed to require modifying the static inverter by replacing
resistor R170 with a new resistor and relocating the new resistor.
Actions Since Issuance of Second Supplemental NPRM
Since issuance of the second supplemental NPRM, Boeing has issued
the revised service bulletins listed in the following table:
Revised Service Bulletins
------------------------------------------------------------------------
Model-- Boeing--
------------------------------------------------------------------------
737-300, -400, -500 series Alert Service Bulletin 737-24A1166,
airplanes. Revision 4, dated May 21, 2009.
757-200, -200CB, -200PF Special Attention Service Bulletin 757-24-
series airplanes. 0110, Revision 1, dated August 6, 2009.
757-300 series airplanes..... Special Attention Service Bulletin 757-24-
0111, Revision 1, dated August 6, 2009.
------------------------------------------------------------------------
No additional work is necessary for airplanes on which the
modification specified in Boeing Alert Service Bulletin 737-24A1166,
Revision 3, dated July 25, 2007, has been done. Revision 4 clarifies
certain sections, moves airplanes from Group 2 to Group 1 in the
effectivity, and removes the Group 2 work instructions.
Boeing Special Attention Service Bulletin 757-24-0110, Revision 1,
dated August 6, 2009, adds an inspection of certain static inverter
part numbers to make sure only approved part numbers are installed;
however, the proposed modification requires modifying the static
inverter by replacing the resistor with a new resistor having an
approved part number. Revision 1 also moves airplanes from Group 2 to
Group 1 in the effectivity, and the Group 2 work instructions were
deleted. Therefore, no additional work is necessary for airplanes
modified in accordance with Boeing Special Attention Service Bulletin
757-24-0110, dated April 28, 2005.
Boeing Special Attention Service Bulletin 757-24-0111, Revision 1,
dated August 6, 2009, also adds an inspection of certain static
inverter part numbers to make sure only approved part numbers are
installed; however, the proposed modification requires modifying the
static inverter by replacing the resistor with a new resistor having an
approved part number. Revision 1 also moves airplanes from Group 2 to
Group 1 in the effectivity, and the Group 2 work instructions were
deleted. No additional work is necessary for airplanes modified in
accordance with Boeing Special Attention Service Bulletin 757-24-0111,
dated April 28, 2005.
We have revised Table 1 of this AD to refer to the latest revisions
of the service bulletins and added a new paragraph (h) to this AD to
give credit for actions done in accordance with the earlier revisions
that were referenced in Table 1 of the NPRM.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received on the
second supplemental NPRM.
Support for the Second Supplemental NPRM
Northwest Airlines has no objection to the second supplemental
NPRM; Boeing concurs with the content of the second supplemental NPRM.
Request To Permit Installation of Static Inverters Having Certain Part
Numbers
American Airlines (AAL) and FedEx Express request that we allow
installation of static inverters having certain part numbers.
AAL asks that we permit installation of static inverters having
part numbers (P/Ns) S282T004-2, -3, and -4. AAL states that those
static inverters do not have an overheating safety concern, which is
the unsafe condition addressed in the second supplemental NPRM. AAL
adds that static inverters that have P/Ns S282T004-2, -3, and -4 are
fully interchangeable on the Model 757 fleet.
FedEx Express asks that Boeing Special Attention Service Bulletin
757-24-0110, dated April 28, 2005, be revised to include Avionics
Instruments static inverters having P/Ns S282T004-28 and S282T004-30 as
acceptable to remain on Model 757 airplanes. FedEx Express adds that
since issuance of the original issue of Boeing Special Attention
Service Bulletin 757-24-0110, those static inverters have been
installed on some Model 757 airplanes and have been added to the Boeing
Illustrated Parts Catalog. FedEx Express notes that P/Ns S282T004-2, -
3, -4, -28, and -30 should be the P/Ns for the static inverters
installed in accordance with the requirements in the second
[[Page 68503]]
supplemental NPRM. FedEx Express adds that combining Groups 1 and 2
into one group would accomplish this task.
We agree with the commenters' requests and provide the following
explanation. As noted previously, Boeing has issued Special Attention
Service Bulletin 757-24-0110, Revision 1, dated August 6, 2009. The
effectivity specified in Revision 1 is changed to move airplanes from
Group 2 to Group 1, and to remove the Group 2 work instructions by
combining Group 2 work instructions with Group 1. The work instructions
specified in Revision 1 also add an inspection for certain static
inverter part numbers that allows for installation of static inverters
having P/Ns S282T004-2, -3, -4, -25, -28, and -30. Inspection of the
static inverter P/Ns will prevent unnecessary replacement of approved
static inverters. We have changed the applicability in paragraph (c) of
this AD to identify Revision 1 of Boeing Special Attention Service
Bulletin 757-24-0110.
Request To Include Revised Service Information
AAL states that it found a discrepancy in Figure 1 of Boeing
Special Attention Service Bulletin 767-24-0160, dated June 30, 2005
(referred to in the second supplemental NPRM), and asks that this
service bulletin be revised to correct the discrepancy. AAL adds that
the discrepancy is in Figure 1, which specifies an inspection of the
static inverter on Groups 1 and 3 airplanes. Figure 2 also contains an
error which specifies the actions are applicable to Group 3 airplanes.
However, Group 2 airplanes are not identified in either of these
figures. AAL also notes that in Boeing Service Message 1-1156909141-2,
Boeing specifies that static inverters having P/Ns S282T004-2, -3, -4
are acceptable for installation across the Model 757 airplane fleet
since the Model 767 airplane fleet uses the same static inverter.
We acknowledge the commenter's concern and agree that the error in
Figure 1 of Boeing Special Attention Service Bulletin 767-24-0160,
dated June 30, 2005, should be corrected in a revision; but we do not
consider that delaying the final rule until after the release of a
future revision is warranted. The original issue of Boeing Special
Attention Service Bulletin 767-24-0160 includes sufficient information
to accomplish the modification of the static inverter. However, we have
added new paragraph (g) to this AD to exclude Group 2 airplanes that
have a static inverter with part number S282T004-2, S282T004-3, or
S282T004-4, from the modification requirement. We have re-identified
subsequent paragraphs accordingly.
Request To Change Cost Impact Section
AAL states that the cost estimate for material and labor necessary
for accomplishing the modification on its airplanes is more than the
estimate in the second supplemental NPRM.
We infer that AAL is asking that the work hours and cost specified
in the Cost Impact section of the AD be increased. We do not agree. The
cost information below describes only the direct costs of the specific
actions required by this AD. Based on the best data available, the
manufacturer provided the number of work hours (up to 2 hours,
depending on airplane configuration) necessary to do the required
actions. This number represents the time necessary to perform only the
actions actually required by this AD. We recognize that, in doing the
actions required by an AD, operators might incur incidental costs in
addition to the direct costs. The cost analysis in AD rulemaking
actions, however, typically does not include incidental costs such as
the time required to gain access and close up, time necessary for
planning, or time necessitated by other administrative actions. Those
incidental costs, which might vary significantly among operators, are
almost impossible to calculate. We have not changed the AD in this
regard.
Request for Clarification
Cargolux Airlines International S.A. states that it has followed
the history of the proposed rule since 2003, and is not aware of any
new event reported on the static inverters since that time. Cargolux
asks for clarification that only one airplane was affected prior to
2003, and no airplanes were affected after 2003. Cargolux also asks for
the number of occurrences of R170 resistors overheating, and the number
of units manufactured.
We acknowledge the commenter's request and provide the following
clarification. Prior to 2003 there were 39 static inverter failures on
39 airplanes; since 2003 there have been 15 inverters on 15 airplanes
that failed due to the R170 resistor overheating, and approximately
9,400 units have been manufactured.
Explanation of Additional Paragraph in the Final Rule
We have added a new paragraph (d) to this AD to provide the Air
Transport Association (ATA) of America code 24: Electrical power. This
code is added to make this AD parallel with other new AD actions. We
have reidentified subsequent paragraphs accordingly.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are approximately 3,856 airplanes of the affected design in
the worldwide fleet. The FAA estimates that 1,882 airplanes of U.S.
registry will be affected by this AD. The following table provides the
estimated costs for U.S. operators to comply with this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per airplane registered Fleet cost
rate per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification................... Up to 2 hours, $80 $0 Between $80 and 1,882 Up to $301,120.
depending on $160.
airplane
configuration.
--------------------------------------------------------------------------------------------------------------------------------------------------------
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if the AD were not adopted. The cost impact figures
discussed in AD rulemaking actions represent only the
[[Page 68504]]
time necessary to perform the specific actions actually required by the
AD. These figures typically do not include incidental costs, such as
the time required to gain access and close up, planning time, or time
necessitated by other administrative 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 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 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 by
adding the following new airworthiness directive (AD):
2009-26-03 Boeing: Amendment 39-16138. Docket No. FAA-2009-0911;
Directorate Identifier 2002-NM-12-AD.
Effective Date
(a) This AD becomes effective February 1, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following airplanes, certificated in
any category, as identified in the applicable Boeing service
bulletin specified in Table 1 of this AD:
Table 1--Applicability
------------------------------------------------------------------------
Model-- Boeing--
------------------------------------------------------------------------
737-600, -700, -700C, -800, - Special Attention Service Bulletin 737-24-
900 series airplanes. 1165, Revision 1, dated October 20,
2005.
737-300, -400, -500 series Alert Service Bulletin 737-24A1166,
airplanes. Revision 4, dated May 21, 2009.
747-400, -400D, -400F series Service Bulletin 747-24-2254, Revision 1,
airplanes. dated March 5, 2007.
757-200, -200CB, -200PF Special Attention Service Bulletin 757-24-
series airplanes. 0110, Revision 1, dated August 6, 2009.
757-300 series airplanes..... Special Attention Service Bulletin 757-24-
0111, Revision 1, dated August 6, 2009.
767-200, -300, -300F series Special Attention Service Bulletin 767-24-
airplanes. 0160, dated June 30, 2005.
767-400ER series airplanes... Special Attention Service Bulletin 767-24-
0161, dated June 30, 2005.
777-200, -300, -300ER series Service Bulletin 777-24-0095, Revision 1,
airplanes. dated January 3, 2007.
------------------------------------------------------------------------
Subject
(d) Air Transport Association (ATA) of America Code 24:
Electrical power.
Unsafe Condition
(e) This AD results from evaluation of the carbon resistor,
which revealed a failure mode that can cause the resistor to ignite,
involving adjacent capacitors as well. The Federal Aviation
Administration is issuing this AD to prevent a standby static
inverter from overheating, which could result in smoke in the flight
deck and cabin and loss of the electrical standby power system.
Modification
(f) At the time specified in paragraph (f)(1) or (f)(2) of this
AD, as applicable: Modify the static inverter by removing resistor
R170 from the logic control card assembly and replacing it with a
new resistor, and relocating the new resistor to the solder side of
the printed circuit board, in accordance with the Accomplishment
Instructions of the applicable service bulletin specified in Table 1
of this AD, except as provided by paragraph (g) of this AD.
(1) For Model 737, 757, and 767 airplanes: Within 42 months
after the effective date of this AD.
(2) For Model 747 and 777 airplanes: Within 60 months after the
effective date of this AD.
(g) For Group 2 airplanes identified Boeing Special Attention
Service Bulletin 767-24-0160, dated June 30, 2005: Airplanes having
a static inverter with part number S282T004-2, S282T004-3, or
S282T004-4, are not required to do the modification specified in
paragraph (f) of this AD.
(h) Actions accomplished before the effective date of this AD in
accordance with the applicable Boeing service bulletin specified in
Table 2 of this AD, are considered acceptable for compliance with
the corresponding actions specified in this AD.
[[Page 68505]]
Table 2--Previously Issued Service Information
----------------------------------------------------------------------------------------------------------------
Boeing -- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
Alert Service Bulletin 737-24A1166...... 3.............................. July 25, 2007.
Special Attention Service Bulletin 757- Original....................... April 28, 2005.
24-0110.
Special Attention Service Bulletin 757- Original....................... April 28, 2005.
24-0111.
----------------------------------------------------------------------------------------------------------------
Note 1: The Boeing service bulletins specified in Table 1 of
this AD refer to Avionic Instruments Inc. Service Bulletins 1-002-
0102-1000-24-28, Revision A, dated June 22, 2005; and Revision B,
dated July 24, 2006; as additional sources of guidance for
accomplishing the modification required by paragraph (f) of this AD.
Alternative Methods of Compliance
(i)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Binh V. Tran, Aerospace Engineer, Systems and Equipment
Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601
Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6485; fax (425) 917-6590. Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
Material Incorporated by Reference
(j) You must use the applicable Boeing service information
contained in Table 3 of this AD to do the actions required by this
AD, unless the AD specifies otherwise.
Table 3--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Boeing-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
Alert Service Bulletin 737-24A1166...... 4.............................. May 21, 2009.
Service Bulletin 747-24-2254............ 1.............................. March 5, 2007.
Service Bulletin 777-24-0095............ 1.............................. January 3, 2007.
Special Attention Service Bulletin 737- 1.............................. October 20, 2005.
24-1165.
Special Attention Service Bulletin 757- 1.............................. August 6, 2009.
24-0110.
Special Attention Service Bulletin 757- 1.............................. August 6, 2009.
24-0111.
Special Attention Service Bulletin 767- Original....................... June 30, 2005.
24-0160.
Special Attention Service Bulletin 767- Original....................... June 30, 2005.
24-0161.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1, fax 206-766-5680; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference 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/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on December 4, 2009.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-29963 Filed 12-24-09; 8:45 am]
BILLING CODE 4910-13-P
