[Federal Register Volume 71, Number 191 (Tuesday, October 3, 2006)]
[Proposed Rules]
[Pages 58323-58325]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-16307]



[[Page 58323]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25973; Directorate Identifier 2006-NM-178-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777 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 all Boeing Model 777 airplanes. This proposed AD would require 
repetitive measurements of the freeplay of the right and left 
elevators, rudder, and rudder tab, and related investigative and 
corrective actions if necessary. This proposed AD would also require 
repetitive lubrications of the elevator, rudder, and rudder tab 
components. This proposed AD results from reports of freeplay-induced 
vibration of unbalanced control surfaces. Excessive freeplay of control 
surfaces can cause unacceptable airframe vibration during flight. The 
potential for vibration of the control surface should be avoided 
because the point of transition from vibration to divergent flutter is 
unknown. We are proposing this AD to prevent flutter, which can cause 
damage to the control surface structure and consequent loss of control 
of the airplane.

DATES: We must receive comments on this proposed AD by November 17, 
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: Dennis Stremick, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6450; 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-
25973; Directorate Identifier 2006-NM-178-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.

Discussion

    We have received reports of freeplay-induced vibration of 
unbalanced control surfaces on Boeing Model 727, 737, 757, and 767 
airplanes. Excessive corrosion and wear of components and/or interfaces 
allows excessive freeplay movement of the control surfaces and can 
cause excessive vibration of the airframe during flight. The potential 
for vibration of the control surface should be avoided because the 
point of transition from vibration to divergent flutter is unknown. 
Flutter can cause damage to the control surface structure during 
flight. This condition, if not corrected, could result in loss of 
control of the airplane.
    The control surfaces on Model 777 airplanes are similar to those on 
the affected Model 727, 737, 757, and 767 airplanes. Therefore, all of 
these models may be subject to the same unsafe condition.

Relevant Service Information

    We have reviewed Boeing Special Attention Service Bulletin 777-27-
0062, dated July 18, 2006. The service bulletin describes procedures 
for measuring the freeplay of the right and left elevators, rudder, and 
rudder tab. If the freeplay is greater than the given limit, the 
service bulletin specifies accomplishing related investigative and 
corrective actions to decrease the freeplay. The related investigative 
actions include inspecting for worn parts, which include hinges, bolts, 
actuator fittings, related bushings, power control unit (PCU) reaction 
links, kick link bearings, and hinge bolts. The corrective actions 
include replacing or repairing any worn parts; and repeating the 
freeplay measurement until the freeplay is less than the specified 
limits. The service bulletin also describes procedures for 
accomplishing repetitive lubrications of the elevator, rudder, and 
rudder tab components. Those components include hinge bearings for the 
elevators, rudder, and rudder tab; and reaction links and PCU rod ends 
for the elevators and rudder. The service bulletin also specifies doing 
the freeplay measurement before the lubrication, when the lubrication 
and freeplay measurement of a part are done during the same maintenance 
period.
    For the initial measurement of the freeplay of the right and left 
elevators, rudder, and rudder tab, the service bulletin specifies that 
the measurements be done within 36 months after the date of the service 
bulletin, or within 36 months after the date of issuance of the 
original standard certificate of airworthiness or original export 
certificate of airworthiness, whichever occurs later. The service 
bulletin specifies a measurement repeat interval of 12,000 flight 
hours, or 36 months, whichever occurs first. The service

[[Page 58324]]

bulletin also specifies that any corrective actions be done before 
further flight.
    For the initial lubrication of the elevator, rudder, and rudder tab 
components, the service bulletin specifies that the lubrications be 
done within 16 months after the date of the service bulletin, or within 
16 months after the date of issuance of the original standard 
certificate of airworthiness or original export certificate of 
airworthiness, whichever occurs later. The service bulletin specifies a 
lubrication repeat interval of 5,000 flight hours, or 16 months, 
whichever occurs first.
    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 695 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs, at 
an average labor rate of $80 per hour, for U.S. operators to comply 
with this proposed AD.

                                                 Estimated Costs
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                                                                              Number of
                                                                                U.S.-
               Action                  Work hours     Cost per airplane      registered         Fleet cost
                                                                              airplanes
----------------------------------------------------------------------------------------------------------------
Measurement of elevators, per                   4  $320, per measurement             145  $46,400, per
 measurement cycle.                                 cycle.                                 measurement cycle.
Lubrication of elevators, per                  17  $1,360, per lubrication           145  $197,200, per
 lubrication cycle.                                 cycle.                                 lubrication cycle.
Measurement of rudder, per                      4  $320, per measurement             145  $46,400, per
 measurement cycle.                                 cycle.                                 measurement cycle.
Lubrication of rudder, per                      7  $560, per lubrication             145  $81,200, per
 lubrication cycle.                                 cycle.                                 lubrication cycle.
Measurement of rudder tab, per                  3  $240, per measurement             145  $34,800, per
 measurement cycle.                                 cycle.                                 measurement cycle.
Lubrication of rudder tab, per                  5  $400, per lubrication             145  $58,000, per
 lubrication cycle.                                 cycle.                                 lubrication cycle.
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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 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-2006-25973; Directorate Identifier 2006-NM-
178-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
17, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 777-200, -200LR, -300, 
and -300ER series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from reports of freeplay-induced vibration 
of unbalanced control surfaces. Excessive freeplay of control 
surfaces can cause unacceptable airframe vibration during flight. 
The potential for vibration of the control surface should be avoided 
because the point of transition from vibration to divergent flutter 
is unknown. We are issuing this AD to prevent flutter, which can 
cause damage to the control surface structure and consequent loss of 
control of the airplane.

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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.

Repetitive Measurements

    (f) At the applicable times specified in Tables 1, 2, and 3 of 
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service 
Bulletin 777-27-0062, dated July 18, 2006, except as provided by 
paragraph (i) of this AD: Measure the freeplay of the right and left 
elevators, rudder, and rudder tab; and do all related investigative 
and corrective actions before further flight; by accomplishing all 
the actions specified in Parts 1, 3, and 5 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 777-27-
0062, dated July 18, 2006, as applicable. Repeat the measurements 
and related investigative and corrective actions thereafter at the 
interval specified in Table 1, 2, or 3 of the service bulletin, as 
applicable.

Repetitive Lubrications

    (g) At the applicable times specified in Tables 1, 2, and 3 of 
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service 
Bulletin 777-27-0062, dated July 18, 2006, except as provided by 
paragraph (i) of this AD: Lubricate the elevator components, rudder 
components, and rudder tab components, by accomplishing all the 
actions specified Parts 2, 4, and 6 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 777-27-
0062, dated July 18, 2006, as applicable. Repeat the lubrications 
thereafter at the interval specified in Table 1, 2, or 3 of the 
service bulletin, as applicable.

Concurrent Compliance Times

    (h) If a freeplay measurement of a specified part required by 
paragraph (f) of this AD and a lubrication of the same part required 
by paragraph (g) of this AD are due at the same time or will be 
accomplished during the same maintenance visit, the freeplay 
measurement and all related investigative and corrective actions 
must be done before the lubrication is accomplished.

Exceptions to Compliance Times

    (i) Where Boeing Special Attention Service Bulletin 777-27-0062, 
dated July 18, 2006, recommends an initial compliance threshold of 
``Within 36 months after the date on this service bulletin'' for 
Parts 1, 3, and 5 of the service bulletin, this AD requires an 
initial compliance threshold of ``within 36 months after the 
effective date of this AD.'' Where Boeing Special Attention Service 
Bulletin 777-27-0062, dated July 18, 2006, recommends an initial 
compliance threshold of ``Within 16 months after the date on this 
service bulletin'' for Parts 2, 4, and 6 of the service bulletin, 
this AD requires an initial compliance threshold of ``within 16 
months after the effective date of this AD.''

Alternative Methods of Compliance (AMOCs)

    (j)(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 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 September 26, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-16307 Filed 10-2-06; 8:45 am]
BILLING CODE 4910-13-P