[Federal Register Volume 75, Number 223 (Friday, November 19, 2010)]
[Proposed Rules]
[Pages 70868-70871]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-29236]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1115; Directorate Identifier 2010-NM-221-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. 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 different electrical
connections, which would terminate the repetitive inspections for that
flightdeck window 1. This proposed AD was prompted by several reports
of electrical arcs at the terminal blocks of the electrically heated
flightdeck window 1. 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 January 3, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed 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 [email protected];
Internet https://www.myboeingfleet.com. You may review copies of the
referenced 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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Louis Natsiopoulos, 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 proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2010-1115;
Directorate Identifier 2010-NM-221-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 http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received multiple reports of electrical arcs at the
terminal blocks of the flightdeck window 1. In several incidents, the
arcs resulted in open flames. An investigation showed that the
electrical arcs are caused by loose terminal connections, which are
caused by incorrect torque of the screw or an incorrectly installed
screw. A loose terminal connection will overheat with electrical
current passing through it. An overheated connector can degrade the
adjacent electrical circuit (including solder, if present). This
condition, 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 Boeing Special Attention Service Bulletin 747-30-
2081, Revision 2, dated March 10, 2010. Boeing Special Attention
Service Bulletin 747-30-2081, Revision 2, dated March 10, 2010,
describes procedures for repetitive detailed inspections for damage
(including but not limited to a cross-threaded screw, arcing, loose
terminal, and heat damage) of the terminal block, connector, and wiring
at the left and right flightdeck window 1, and corrective actions if
necessary. The corrective actions are applying the correct torque to a
loose electrical connection, repairing damaged wiring, or installing a
replacement window 1. Boeing Special Attention Service Bulletin 747-30-
2081, Revision 2, dated March 10, 2010, specifies a compliance time of
within 500 hours after the date on the service bulletin for doing the
initial detailed inspection.
Boeing Special Attention Service Bulletin 747-30-2081, Revision 2,
dated March 10, 2010, specifies that the replacement window can either
be a window that uses screws and lugs for the electrical connection or
a window that uses pins and sockets for the electrical connections. For
airplanes on which a replacement window that uses pins and sockets is
installed, Boeing Special Attention Service Bulletin 747-30-2081,
Revision 2, dated March 10, 2010, also specifies changes to the related
wire bundle. Boeing Special Attention Service Bulletin 747-30-2081,
Revision 2, dated March 10, 2010, specifies that installing a window
that uses pins and sockets eliminates the need for the repetitive
inspections. If the window is replaced with the same type of window
(i.e., windows with the screw and lug type electrical terminations),
then the inspection must be repeated within 500 flight hours from
[[Page 70869]]
the date of the accomplishment of these corrective actions and every
6,000 flight hours thereafter.
Related Rulemaking
We issued AD 2010-15-01, Amendment 39-16367 (75 FR 39804, July 13,
2010), that applies to certain Model 757 airplanes, Model 767
airplanes, and Model 777-200 and -300 series airplanes. That AD
requires repetitive inspections for damage (e.g., of the electrical
terminal at the left and right flightdeck window 1), and corrective
actions if necessary. That AD also allows for replacing the flightdeck
window 1 with a new improved flightdeck window equipped with different
electrical connections, which terminates the repetitive inspections for
that flightdeck window 1. That AD results from several reports of
electrical arcs at the terminal blocks of the electrically heated
flightdeck window 1. We issued that AD to prevent smoke and fire in the
cockpit, which could lead to loss of visibility, and injuries to or
incapacitation of the flightcrew.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between the Proposed AD and the Service
Information.''
Differences Between the Proposed AD and the Service Information
Boeing Special Attention Service Bulletin 747-30-2081, Revision 2,
dated March 10, 2010, does not explicitly specify an inspection for,
nor specify a corrective action for, airplanes on which a screw is
found cross threaded during the detailed inspections in paragraph (g)
of this proposed AD. If these conditions are found, paragraph (i) of
this proposed AD would require replacing the windshield either before
further flight if the screw is found to be loose, or within 500 flight
hours or 150 days after the inspection if the screw is found to be
tight, whichever occurs first.
Where Boeing Special Attention Service Bulletin 747-30-2081,
Revision 2, dated March 10, 2010, specifies an interval for repetitive
inspections not to exceed 6,000 flight hours, paragraphs (g) and (h) of
this proposed AD would require repetitive inspections at intervals not
to exceed 6,000 flight hours or 24 months, whichever occurs later. We
have determined that this revised interval will not adversely affect
safety of the affected airplanes. Boeing concurs with this extension of
the interval for the repetitive inspections.
Clarifications of Service Information
Where Boeing Special Attention Service Bulletin 747-30-2081,
Revision 2, dated March 10, 2010, and paragraph (h) of this proposed AD
state to perform a detailed inspection for damage of the terminal
block, connector, and wiring of flightdeck window 1 ``within 500 flight
hours,'' it is also acceptable to do the inspection at zero flight
hours (i.e., before the airplane ever leaves the hangar and resumes
operations). The intent of this second inspection is for quality
assurance purposes. This clarification has been coordinated with
Boeing.
We have added paragraph (k) of this proposed AD to clarify that
each window is handled separately. In the compliance table in paragraph
1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 747-
30-2081, Revision 2, dated March 10, 2010, the repeat interval applies
to the action, which is doing both Work Packages 1 and 2. If the left
window is replaced with a window that uses pins and sockets for the
electrical connection, then that replacement terminates the
requirements of this proposed AD for that window only. The other window
still needs to be inspected.
Costs of Compliance
We estimate that this proposed AD will affect 251 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Action Labor cost Parts cost Cost per product Cost on U.S. operators
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Inspection................. 1 work-hour x $85 per None....................... $85 per inspection $21,335 per inspection cycle.
hour = $85 per cycle.
inspection cycle.
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We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
these replacements:
On-Condition Costs
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Action Labor cost Parts cost Cost per product
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Replacement of windshield......... Up to 18 work-hours x Up to $47,592........ Up to $49,122.
$85 per hour =
$1,530.
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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
[[Page 70870]]
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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
The Boeing Company: Docket No. FAA-2010-1115; Directorate Identifier
2010-NM-221-AD.
Comments Due Date
(a) We must receive comments by January 3, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes, certificated
in any category; as identified in Boeing Special Attention Service
Bulletin 747-30-2081, Revision 2, dated March 10, 2010.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 30: Ice and rain protection.
Unsafe Condition
(e) This AD results from several reports of electrical arcs at
the terminal blocks of the electrically heated flightdeck window 1.
In several 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
(f) Comply with this AD within the compliance times specified,
unless already done.
Detailed Inspection and Corrective Actions
(g) Within 500 flight hours after the effective date of this AD,
do a detailed inspection for damage (including but not limited to a
cross-threaded screw, arcing, loose terminal, and heat damage) of
the terminal block, connector, and wiring of flightdeck window 1,
and do all applicable corrective actions, by accomplishing the
actions specified in Work Packages 1 and 2 of Boeing Special
Attention Service Bulletin 747-30-2081, Revision 2, dated March 10,
2010, except as provided by paragraph (j) of this AD. Do all
applicable corrective actions before further flight, except as
required by paragraph (i) of this AD. Except as required by
paragraphs (h) and (i) of this AD, repeat the detailed inspection
thereafter at intervals not to exceed 6,000 flight hours or 24
months, whichever occurs later. Doing the replacement specified in
paragraph (k) of this AD terminates the repetitive inspection
requirements of this paragraph for the replaced flightdeck window 1.
(h) For airplanes on which a flightdeck window 1 is replaced
with a window that uses screws and lugs for the electrical
connections, in accordance with Work Package 1 or 2 of Boeing
Special Attention Service Bulletin 747-30-2081, Revision 2, dated
March 10, 2010: Except as provided by paragraph (j) of this AD, 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 or 24 months, whichever occurs
later. Doing the replacement specified in paragraph (k) of this AD
terminates the repetitive inspection requirements of this paragraph
for the replaced flightdeck window 1.
Exceptions to the Service Bulletin
(i) If, during the inspection required by paragraph (g) of this
AD, a screw is found cross threaded do the applicable corrective
action specified in paragraph (i)(1) or (i)(2) of this AD.
(1) If the terminal lug is loose and cannot be tightened: Before
further flight, replace the window, in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-30-2081, Revision 2, dated March 10, 2010.
(2) If the terminal lug is tight: Within 150 days or 500 flight
hours after the inspection, whichever occurs first, replace the
window, in accordance with the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747-30-2081, Revision 2, dated
March 10, 2010.
(j) Where paragraph 1.E. of Boeing Special Attention Service
Bulletin 747-30-2081, Revision 2, dated March 10, 2010, states in
the ``Action'' column to ``do the inspections given in Work Packages
1 and 2,'' the intent is ``Work Package 1, step 3. or Work Package
2, step 3., as applicable.'' Operators are to use one or the other
(or both) work instruction, as applicable, to replace the window(s)
that need replacing.
Optional Terminating Action
(k) 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 Boeing Special Attention Service Bulletin
747-30-2081, Revision 2, dated March 10, 2010, ends the repetitive
inspection requirements of this AD for that window only.
Credit for Actions Accomplished Previously According to Previous Issue
of Service Information
(l) Actions accomplished before the effective date of this AD in
accordance with Boeing Special Attention Service Bulletin 747-30-
2081, dated August 08, 2006; or Revision 1, dated August 20, 2008;
are considered acceptable for compliance with the corresponding
actions specified in 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 using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the ACO, send it to the attention of the
person identified in the Related Information section of this AD.
Information may be e-mailed to: [email protected].
(2) Before using any approved AMOC, notify your Principal
Maintenance Inspector or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector, your local Flight
Standards District Office.
Related Information
(n) For more information about this AD, contact Louis
Natsiopoulos, 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; e-mail: [email protected].
(o) 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
[email protected]; Internet https://www.myboeingfleet.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, the FAA, 1601 Lind Avenue, SW.,
Renton, Washington. For information on the availability of this
material at the FAA, call 425-227-1221.
[[Page 70871]]
Issued in Renton, Washington, on November 10, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-29236 Filed 11-18-10; 8:45 am]
BILLING CODE 4910-13-P