Document ID: FAA-2010-1115-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Boeing Co. Model 747 100, 747 100B, 747 100B SUD, 747 200B, 747 200C, 747 200F, etc. Series Airplanes
Posted Date: 2010-11-19T05:00Z

[Federal Register Volume 75, Number 223 (Friday, November 19, 2010)]
[Proposed Rules]
[Pages 70868-70871]
From the Federal Register Online via the Government Printing 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 me.boecom@boeing.com; 
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
--------------------------------------------------------------------------------------------------------------------------------------------------------
           Action                  Labor cost                 Parts cost             Cost per product                 Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection.................  1 work-hour x $85 per   None.......................  $85 per inspection      $21,335 per inspection cycle.
                              hour = $85 per                                       cycle.
                              inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
              Action                      Labor cost             Parts cost              Cost per product
----------------------------------------------------------------------------------------------------------------
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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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: Elias.Natsiopoulos@faa.gov.
    (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 
me.boecom@boeing.com; 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