[Federal Register Volume 71, Number 102 (Friday, May 26, 2006)]
[Proposed Rules]
[Pages 30338-30340]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-8123]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24891; Directorate Identifier 2006-NM-080-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777-200, -300, and -300ER 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 777-200, -300, and -300ER series airplanes. 
This proposed AD would require replacement of the gimbal plates of the 
left and right outboard trailing edge flaps with improved gimbal plates 
and other specified actions. This proposed AD results from a broken 
pivot link found on the inboard support for the outboard trailing edge 
flap. We are proposing this AD to prevent disconnection of the drive 
arm from its drive gimbal, due to a broken pivot link on an outboard 
flap support, which could result in unexpected roll of the airplane and 
loss of control of the airplane.

DATES: We must receive comments on this proposed AD by July 10, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6443; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
24891; Directorate Identifier 2006-NM-080-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 http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

[[Page 30339]]

Discussion

    We have received a report indicating that a broken pivot link was 
found on the inboard support for the outboard trailing edge flap on a 
Boeing Model 777-300 series airplane. That broken pivot link was found 
after an incident where, during approach, the flightcrew received the 
FLAPS PRIMARY and FLAPS SKEW messages, and the airplane rolled slightly 
to the left. The flightcrew was able to land the airplane without 
difficulty. Investigation revealed that a broken pivot link on outboard 
flap support number 2 caused an increased load on the drive arm 
assembly of support number 1. The increased load caused the drive arm 
gimbal plates to disconnect from the drive gimbal, which led to a 
skewed outboard flap. This condition, if not corrected, could result in 
unexpected roll of the airplane and loss of control of the airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 777-27A0073, dated 
March 30, 2006. The service bulletin describes procedures for replacing 
the gimbal plates of the left and right outboard trailing edge flaps 
with improved gimbal plates and doing other specified actions. The 
other specified actions include adjusting the gimbal plate shims, 
rotating the upper gimbal bushing, installing a new grease fitting, 
adjusting the bulkhead fitting shim, changing the flap skew detection 
bracket assembly, lubricating the outboard transmission, ballscrews, 
and gimbal of the outboard flaps, and doing the adjustment/test of the 
trailing edge flap system. Accomplishing the actions specified in the 
service information is intended to adequately address the unsafe 
condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously.

Costs of Compliance

    There are about 546 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 145 airplanes of 
U.S. registry. The proposed actions would take about 153 work hours per 
airplane, at an average labor rate of $80 per work hour. Required parts 
would cost about $69,850 per airplane. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $11,903,050, or 
$82,090 per airplane.

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 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 that the 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed 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, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

BOEING: Docket No. FAA-2006-24891; Directorate Identifier 2006-NM-
080-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 10, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 777-200, -300, and -300ER 
series airplanes, certificated in any category; as identified in 
Boeing Alert Service Bulletin 777-27A0073, dated March 30, 2006.

Unsafe Condition

    (d) This AD results from a broken pivot link found on the 
inboard support for the outboard trailing edge flap. We are issuing 
this AD to prevent disconnection of the drive arm from its drive 
gimbal, due to a broken pivot link on an outboard flap support, 
which could result in unexpected roll of the airplane and loss of 
control of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Replacement of Gimbal Plates

    (f) Within 24 months after the effective date of this AD, 
replace the gimbal plates of the left and right outboard trailing 
edge flaps with improved gimbal plates, and do the other specified 
actions before further flight after the replacement, by 
accomplishing all the actions specified in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 777-27A0073, dated 
March 30, 2006.

Parts Installation

    (g) As of the effective date of this AD, no person may install a 
gimbal plate, part numbers 113W1112-3, 113W1112-4, 113W1212-3, and 
113W1212-4, on any airplane, unless it has been modified in 
accordance with paragraph (f) of this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA

[[Page 30340]]

Flight Standards Certificate Holding District Office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.

    Issued in Renton, Washington, on May 18, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-8123 Filed 5-25-06; 8:45 am]
BILLING CODE 4910-13-P