Airworthiness Directives; Boeing Model 757 Airplanes, Model 767 Airplanes, and Model 777-200 and -300 Series Airplanes, 13483-13486 [E8-5011]
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Federal Register / Vol. 73, No. 50 / Thursday, March 13, 2008 / Proposed Rules
or Figure 2, as applicable, of Boeing Service
Bulletin 747–27A2397, Revision 2, dated
September 1, 2005.
Action if Cracking Is Found
(i) If any cracking is found during any
inspection required by paragraph (g) of this
AD: Before further flight, do the action in
paragraph (i)(1) or (i)(2) of this AD.
(1) Replace the affected PCM with a new
or serviceable PCM in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–27A2397, Revision 2,
dated September 1, 2005.
(2) Replace the PCM with a PCM that has
the new secondary retention device installed
as specified in paragraph (j) of this AD.
Terminating Action
(j) Within 24 months or 8,400 flight hours
after the effective date of this AD, whichever
occurs earlier: Install a new secondary
retention device for the yaw damper piston
assembly in both the upper and lower PCMs
by either replacing the existing PCM with a
new improved PCM that already has the new
secondary retention device, or by modifying,
testing, and re-identifying the existing PCM.
Do the installation in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–27A2479, dated
November 8, 2007. Doing the installation
terminates the inspection requirements of
this AD.
Note 1: Boeing Alert Service Bulletin 747–
27A2479 refers to Parker Service Bulletins
332700–27–312 and 333200–27–314, both
dated September 13, 2007, as additional
sources of service information for modifying
the PCM.
Prior Accomplishment of Requirements
(k) Actions accomplished before October
13, 2006 (the effective date of AD 2006–18–
17), in accordance with Boeing Alert Service
Bulletin 747–27A2397, dated July 24, 2003;
or Revision 1, dated March 31, 2005; are
considered acceptable for compliance with
the corresponding requirements of this AD.
rwilkins on PROD1PC63 with PROPOSALS
Parts Installation
(l) As of October 13, 2006 no person may
install on any airplane a rudder PCM having
a top assembly part number (P/N) 332700–
1003, –1005, or –1007; or P/N 333200–1003,
–1005, or –1007; unless the PCM has been
ultrasonically inspected and found to be
without cracks; in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–27A2397, Revision 2,
dated September 1, 2005, as specified by
paragraph (g) of this AD.
Alternative Methods of Compliance
(AMOCs)
(m)(1) The Manager, Seattle 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
VerDate Aug<31>2005
16:23 Mar 12, 2008
Jkt 214001
13483
DEPARTMENT OF TRANSPORTATION
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in
accordance with AD 2006–18–17 are
approved as AMOCs for the corresponding
provisions of paragraphs (g), (h), and (i) of
this AD.
Issued in Renton, Washington, on March 4,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–5013 Filed 3–12–08; 8:45 am]
BILLING CODE 4910–13–P
[Docket No. FAA–2008–0274; Directorate
Identifier 2008–NM–038–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757 Airplanes, Model 767
Airplanes, and Model 777–200 and
–300 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Boeing Model 757 airplanes, Model 767
airplanes, and Model 777–200 and –300
series airplanes. This proposed AD
would require repetitive inspections for
damage of the electrical terminal at the
left and right flightdeck window # 1,
and corrective actions if necessary. This
proposed AD would also allow for
replacing the flightdeck window # 1
with a new improved flightdeck
window equipped with electrical
connections, which would end the need
for the repetitive inspections for that
flightdeck window # 1. This proposed
AD results from several reports of
electrical arcs at the terminal blocks of
the electrically heated flightdeck
window # 1. In more than one of the
incidents, the arcs resulted in open
flames. We are proposing this AD to
prevent smoke and fire in the cockpit,
which could lead to loss of visibility,
and injuries to or incapacitation of the
flightcrew.
DATES: We must receive comments on
this proposed AD by April 28, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
SUMMARY:
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FOR FURTHER INFORMATION CONTACT:
Louis Natsiopolous, Aerospace
Engineer, Systems and Equipment
Branch, ANM–130S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6478;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0274; Directorate Identifier
2008–NM–038–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
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Federal Register / Vol. 73, No. 50 / Thursday, March 13, 2008 / Proposed Rules
Discussion
We have received nine reports of
electrical arcs at the terminal blocks of
the flightdeck window #1. In more than
one incident, the arcs resulted in open
flames. An investigation showed that
the electrical arcs are caused by loose
terminal connections in the left and
right flightdeck window # 1 that use
screw and lug electrical heat
terminations. Arcing occurs due to
improper torque or cross-threading of
the screw. The window was redesigned
in 2004 to include electrical heat
terminals that use pin and socket
connections rather than screws and
lugs. Electrical arcs at the terminal
blocks of the flightdeck window # 1, if
not corrected, could result in smoke and
fire in the cockpit, and consequent loss
of visibility, and injuries to or
incapacitation of the flightcrew.
Relevant Service Information
We have reviewed the service
bulletins listed in the table below.
BOEING SERVICE BULLETINS
Boeing Special Attention Service Bulletin
757–30–0019,
757–30–0020,
767–30–0039,
767–30–0041,
777–30–0012,
Boeing model
Revision 1, dated December 19, 2007 ............................
Revision 1, dated December 19, 2007 ............................
dated December 5, 2007 .................................................
dated December 5, 2007 .................................................
Revision 2, dated December 19, 2007 ............................
The service bulletins describe
procedures for repetitive detailed
inspections for damage (including
arcing, loose terminal, or heat damage)
of the electrical terminal (J5 terminal) at
the left and right flightdeck window # 1,
and corrective actions if necessary. The
corrective actions are applying correct
torque to a loose electrical connection,
repairing damaged wiring, or installing
a new window # 1. The service bulletins
specify that the replacement window
can either be a new or serviceable
window that uses screws and lugs for
the electrical connection, or a new
window that uses pins and sockets for
the electrical connections. For airplanes
on which a new window that uses pins
and sockets is installed, the service
bulletins also specify changes to the
757–200, –200CB, and –200PF series airplanes.
757–300 series airplanes.
767–200, –300, and –300F series airplanes.
767–400ER series airplanes.
777–200 and –300 series airplanes.
Difference Between the Proposed AD
and the Service Information
related wire bundle. The service
bulletins specify that installing a new
window that uses pins and sockets
would eliminate the need for the
repetitive inspections.
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the(se)
same type design(s). This proposed AD
would require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Difference
Between the Proposed AD and the
Service Information.’’
The service bulletins do not include
inspection information for airplanes on
which a screw is tightened as part of a
corrective action. This proposed AD
would specify doing the next detailed
inspection within 500 flight hours after
the tightening of the screw, and then
repeating the inspection thereafter at
intervals not to exceed 6,000 flight
hours.
Costs of Compliance
We estimate that this proposed AD
would affect 1,212 airplanes of U.S.
registry. The following table provides
the estimated costs for U.S. operators to
comply with this proposed AD. The
average labor rate is $80 per work hour.
ESTIMATED COSTS
Work
hours
Parts
Cost per product
Inspection ............
rwilkins on PROD1PC63 with PROPOSALS
Action
1
None
$80, per inspection cycle ...........................................
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
VerDate Aug<31>2005
16:23 Mar 12, 2008
Jkt 214001
Fleet cost
$96,960, per inspection cycle.
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
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1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
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Federal Register / Vol. 73, No. 50 / Thursday, March 13, 2008 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
§ 39.13
(b) None.
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Boeing: Docket No. FAA–2008–0274;
Directorate Identifier 2008–NM–038–AD.
PART 39—AIRWORTHINESS
DIRECTIVES
Affected ADs
Applicability
(c) This AD applies to the airplanes
identified in Table 1 of this AD, certificated
in any category.
Comments Due Date
1. The authority citation for part 39
continues to read as follows:
(a) We must receive comments by April 28,
2008.
TABLE 1.—AIRPLANES AFFECTED BY THIS AD
Boeing model—
As identified in Boeing Special Attention Service Bulletin—
757–200, ¥200CB, and ¥200PF series airplanes .................................
757–300 series airplanes .........................................................................
767–200, ¥300, and ¥300F series airplanes ........................................
767–400ER series airplanes ....................................................................
777–200 and ¥300 series airplanes .......................................................
Unsafe Condition
(d) This AD results from several reports of
electrical arcs at the terminal blocks of the
electrically heated flightdeck window #1. In
more than one of the incidents, the arcs
resulted in open flames. We are issuing this
AD to prevent smoke and fire in the cockpit,
which could lead to loss of visibility, and
injuries to or incapacitation of the flightcrew.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Service Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of the applicable service bulletin
listed in Table 1 of this AD.
Inspection and Corrective Actions
(g) Within 500 flight hours after the
effective date of this AD, do a detailed
757–30–0019,
757–30–0020,
767–30–0039,
767–30–0041,
777–30–0012,
Revision 1, dated December 19, 2007.
Revision 1, dated December 19, 2007.
dated December 5, 2007.
dated December 5, 2007.
Revision 2, dated December 19, 2007.
inspection for damage (including arcing,
loose terminal, or heat damage) of the
electrical terminal (J5 terminal) at the left and
right flightdeck window #1, and do all
applicable corrective actions, by
accomplishing all the actions specified in
Work Packages 1 and 2 of the applicable
service bulletin. Do all applicable corrective
actions before further flight. Except as
provided by paragraph (h) of this AD, repeat
the detailed inspection thereafter at intervals
not to exceed 6,000 flight hours. Doing the
replacement specified in paragraph (i) of this
AD terminates the repetitive inspection
requirements of this paragraph for the
replaced flightdeck window #1.
(h) For airplanes on which a corrective
action—either replacement with a new
window #1 that uses screws and lugs for the
electrical connections, or tightening a loose
screw—is done in accordance with Work
Package 1 or 2 of the service bulletin: Do the
next detailed inspection within 500 flight
hours after the corrective action, and repeat
the inspection thereafter at intervals not to
exceed 6,000 flight hours. Doing the
replacement specified in paragraph (i) of this
AD terminates the repetitive inspection
requirements of this paragraph for the
replaced flightdeck window #1.
Optional Terminating Action
(i) Replacing a flightdeck window #1 that
uses screws and lugs for the electrical
connections with a flightdeck window that
uses pins and sockets for the electrical
connections in accordance with Work
Packages 3 or 4 of the service bulletin ends
the repetitive inspection requirements of this
AD for that window #1.
Actions Accomplished Previously
(j) Actions done before the effective date of
this AD in accordance with the applicable
service bulletin specified in Table 2 of this
AD are acceptable for compliance with the
corresponding requirements of this AD.
TABLE 2.—ACCEPTABLE SERVICE BULLETINS
Revision
level
Boeing Special Attention Service Bulletin
757–30–0019
757–30–0020
777–30–0012
777–30–0012
.....................................................................................................................................................
.....................................................................................................................................................
.....................................................................................................................................................
.....................................................................................................................................................
rwilkins on PROD1PC63 with PROPOSALS
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Louis Natsiopolous, Aerospace Engineer,
Systems and Equipment Branch, ANM–130S,
1601 Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6478; fax
(425) 917–6590; has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
VerDate Aug<31>2005
18:03 Mar 12, 2008
Jkt 214001
(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.
PO 00000
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Original ........
Original ........
Original ........
1 ..................
Date
July 19, 2006.
July 19, 2006.
April 15, 2004.
June 2, 2006.
Issued in Renton, Washington, on March 5,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–5011 Filed 3–12–08; 8:45 am]
BILLING CODE 4910–13–P
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Federal Register / Vol. 73, No. 50 / Thursday, March 13, 2008 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0306; Directorate
Identifier 2008–CE–014–AD]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Model 525 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
rwilkins on PROD1PC63 with PROPOSALS
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Cessna Aircraft Company (Cessna)
Model 525 airplanes. This proposed AD
would require you to inspect for missing
firewall sealant between the aft firewall
assembly and seal assembly; and, if you
find that firewall sealant is missing, seal
with firewall sealant between the aft
firewall assembly and seal assembly.
This proposed AD results from a report
that firewall sealant may not have been
applied between the aft firewall
assembly and seal assembly during
manufacture of certain Model 525
airplanes. We are proposing this AD to
detect and correct missing firewall
sealant between the aft firewall
assembly and seal assembly, which
could result in failure of the fire
extinguishing system to prevent the
spread of fire through the firewall gap.
This failure could lead to an
uncontrolled fire.
DATES: We must receive comments on
this proposed AD by May 12, 2008.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
VerDate Aug<31>2005
18:03 Mar 12, 2008
Jkt 214001
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Cessna
Aircraft Company, Product Support,
P.O. Box 7706, Wichita, Kansas 67277;
telephone: (316) 517–5800; fax: (316)
942–9006.
FOR FURTHER INFORMATION CONTACT:
James Galstad, Aerospace Engineer,
Wichita Aircraft Certification Office,
1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4135; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number, ‘‘FAA–2008–0306; Directorate
Identifier 2008–CE–014–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
concerning this proposed AD.
Discussion
We have received a report that
firewall sealant may not have been
applied between the aft firewall
assembly and seal assembly during
manufacture of Model 525 airplanes,
serial numbers 525–0600 through 525–
0662.
A nacelle fire may pass through the
gap where the firewall sealant is
missing. Although the fire detection
system and fire extinguishing system
remain operational, the effectiveness of
the fire extinguishing system has not
been shown to prevent the spread of fire
through the firewall gap. The fire could
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Sfmt 4702
pass through the gap in the firewall or
the effectiveness of the fire
extinguishing system be defeated by the
gap.
This condition, if not corrected, could
result in an uncontrolled fire.
Relevant Service Information
We have reviewed Cessna Aircraft
Company Citation Service Letter SL525–
71–05, Revision 1, dated February 6,
2008. The service information describes
procedures for:
• Inspecting for missing firewall
sealant between the aft firewall
assembly and seal assembly; and
• Sealing with firewall sealant
between the aft firewall assembly and
seal assembly.
FAA’s Determination and Requirements
of the Proposed AD
We are proposing this AD because we
evaluated all information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. This proposed AD would
require you to inspect for missing
firewall sealant between the aft firewall
assembly and seal assembly; and, if you
find that firewall sealant is missing, seal
with firewall sealant between the aft
firewall assembly and seal assembly.
Differences Between This Proposed AD
and the Service Information
The service information requires
compliance within 600 hours time-inservice (TIS) or 1 year after the date of
receipt, whichever occurs first. Due to
the severity of the safety issue
(uncontrolled fire), this proposed AD
has a compliance of within the next 60
hours TIS after the effective date of this
AD or 60 days after the effective date of
this AD, whichever occurs first. The
requirements of this proposed AD, if
adopted as a final rule, would take
precedence over the provisions in the
service information.
Costs of Compliance
We estimate that this proposed AD
would affect 45 airplanes in the U.S.
registry.
We estimate the following costs to do
the proposed inspection:
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]]>Agencies
[Federal Register Volume 73, Number 50 (Thursday, March 13, 2008)]
[Proposed Rules]
[Pages 13483-13486]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-5011]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0274; Directorate Identifier 2008-NM-038-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 757 Airplanes, Model 767
Airplanes, and Model 777-200 and -300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Boeing Model 757 airplanes, Model 767 airplanes, and Model 777-
200 and -300 series airplanes. This proposed AD would require
repetitive inspections for damage of the electrical terminal at the
left and right flightdeck window 1, and corrective actions if
necessary. This proposed AD would also allow for replacing the
flightdeck window 1 with a new improved flightdeck window
equipped with electrical connections, which would end the need for the
repetitive inspections for that flightdeck window 1. This
proposed AD results from several reports of electrical arcs at the
terminal blocks of the electrically heated flightdeck window
1. In more than one of the incidents, the arcs resulted in open flames.
We are proposing this AD to prevent smoke and fire in the cockpit,
which could lead to loss of visibility, and injuries to or
incapacitation of the flightcrew.
DATES: We must receive comments on this proposed AD by April 28, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Louis Natsiopolous, Aerospace
Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6478; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0274;
Directorate Identifier 2008-NM-038-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
[[Page 13484]]
Discussion
We have received nine reports of electrical arcs at the terminal
blocks of the flightdeck window 1. In more than one incident,
the arcs resulted in open flames. An investigation showed that the
electrical arcs are caused by loose terminal connections in the left
and right flightdeck window 1 that use screw and lug
electrical heat terminations. Arcing occurs due to improper torque or
cross-threading of the screw. The window was redesigned in 2004 to
include electrical heat terminals that use pin and socket connections
rather than screws and lugs. Electrical arcs at the terminal blocks of
the flightdeck window 1, if not corrected, could result in
smoke and fire in the cockpit, and consequent loss of visibility, and
injuries to or incapacitation of the flightcrew.
Relevant Service Information
We have reviewed the service bulletins listed in the table below.
Boeing Service Bulletins
------------------------------------------------------------------------
Boeing Special Attention Service
Bulletin Boeing model
------------------------------------------------------------------------
757-30-0019, Revision 1, dated December 757-200, -200CB, and -200PF
19, 2007. series airplanes.
757-30-0020, Revision 1, dated December 757-300 series airplanes.
19, 2007.
767-30-0039, dated December 5, 2007.... 767-200, -300, and -300F series
airplanes.
767-30-0041, dated December 5, 2007.... 767-400ER series airplanes.
777-30-0012, Revision 2, dated December 777-200 and -300 series
19, 2007. airplanes.
------------------------------------------------------------------------
The service bulletins describe procedures for repetitive detailed
inspections for damage (including arcing, loose terminal, or heat
damage) of the electrical terminal (J5 terminal) at the left and right
flightdeck window 1, and corrective actions if necessary. The
corrective actions are applying correct torque to a loose electrical
connection, repairing damaged wiring, or installing a new window
1. The service bulletins specify that the replacement window
can either be a new or serviceable window that uses screws and lugs for
the electrical connection, or a new window that uses pins and sockets
for the electrical connections. For airplanes on which a new window
that uses pins and sockets is installed, the service bulletins also
specify changes to the related wire bundle. The service bulletins
specify that installing a new window that uses pins and sockets would
eliminate the need for the repetitive inspections.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the(se) same type
design(s). This proposed AD would require accomplishing the actions
specified in the service information described previously, except as
discussed under ``Difference Between the Proposed AD and the Service
Information.''
Difference Between the Proposed AD and the Service Information
The service bulletins do not include inspection information for
airplanes on which a screw is tightened as part of a corrective action.
This proposed AD would specify doing the next detailed inspection
within 500 flight hours after the tightening of the screw, and then
repeating the inspection thereafter at intervals not to exceed 6,000
flight hours.
Costs of Compliance
We estimate that this proposed AD would affect 1,212 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD. The average labor rate
is $80 per work hour.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Work
Action hours Parts Cost per product Fleet cost
----------------------------------------------------------------------------------------------------------------
Inspection........................... 1 None.......... $80, per inspection $96,960, per inspection
cycle. cycle.
----------------------------------------------------------------------------------------------------------------
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979), and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
[[Page 13485]]
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Boeing: Docket No. FAA-2008-0274; Directorate Identifier 2008-NM-
038-AD.
Comments Due Date
(a) We must receive comments by April 28, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes identified in Table 1 of
this AD, certificated in any category.
Table 1.--Airplanes Affected by This AD
------------------------------------------------------------------------
As identified in Boeing Special
Boeing model-- Attention Service Bulletin--
------------------------------------------------------------------------
757-200, -200CB, and -200PF series 757-30-0019, Revision 1, dated
airplanes. December 19, 2007.
757-300 series airplanes............... 757-30-0020, Revision 1, dated
December 19, 2007.
767-200, -300, and -300F series 767-30-0039, dated December 5,
airplanes. 2007.
767-400ER series airplanes............. 767-30-0041, dated December 5,
2007.
777-200 and -300 series airplanes...... 777-30-0012, Revision 2, dated
December 19, 2007.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from several reports of electrical arcs at
the terminal blocks of the electrically heated flightdeck window
1. In more than one of the incidents, the arcs resulted in
open flames. We are issuing this AD to prevent smoke and fire in the
cockpit, which could lead to loss of visibility, and injuries to or
incapacitation of the flightcrew.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the applicable service bulletin
listed in Table 1 of this AD.
Inspection and Corrective Actions
(g) Within 500 flight hours after the effective date of this AD,
do a detailed inspection for damage (including arcing, loose
terminal, or heat damage) of the electrical terminal (J5 terminal)
at the left and right flightdeck window 1, and do all
applicable corrective actions, by accomplishing all the actions
specified in Work Packages 1 and 2 of the applicable service
bulletin. Do all applicable corrective actions before further
flight. Except as provided by paragraph (h) of this AD, repeat the
detailed inspection thereafter at intervals not to exceed 6,000
flight hours. Doing the replacement specified in paragraph (i) of
this AD terminates the repetitive inspection requirements of this
paragraph for the replaced flightdeck window 1.
(h) For airplanes on which a corrective action--either
replacement with a new window 1 that uses screws and lugs
for the electrical connections, or tightening a loose screw--is done
in accordance with Work Package 1 or 2 of the service bulletin: Do
the next detailed inspection within 500 flight hours after the
corrective action, and repeat the inspection thereafter at intervals
not to exceed 6,000 flight hours. Doing the replacement specified in
paragraph (i) of this AD terminates the repetitive inspection
requirements of this paragraph for the replaced flightdeck window
1.
Optional Terminating Action
(i) Replacing a flightdeck window 1 that uses screws
and lugs for the electrical connections with a flightdeck window
that uses pins and sockets for the electrical connections in
accordance with Work Packages 3 or 4 of the service bulletin ends
the repetitive inspection requirements of this AD for that window
1.
Actions Accomplished Previously
(j) Actions done before the effective date of this AD in
accordance with the applicable service bulletin specified in Table 2
of this AD are acceptable for compliance with the corresponding
requirements of this AD.
Table 2.--Acceptable Service Bulletins
------------------------------------------------------------------------
Boeing Special Attention
Service Bulletin Revision level Date
------------------------------------------------------------------------
757-30-0019................. Original........ July 19, 2006.
757-30-0020................. Original........ July 19, 2006.
777-30-0012................. Original........ April 15, 2004.
777-30-0012................. 1............... June 2, 2006.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Louis Natsiopolous, Aerospace Engineer, Systems and
Equipment Branch, ANM-130S, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6478; fax (425) 917-6590;
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on March 5, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-5011 Filed 3-12-08; 8:45 am]
BILLING CODE 4910-13-P
