Airworthiness Directives; Boeing Model 767 Airplanes, 6415-6417 [E6-1686]

Download as PDF Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Internal Inspection and Repair Aerospatiale: Docket No. FAA–2006–23816; Directorate Identifier 2005–NM–247–AD. Comments Due Date (a) The FAA must receive comments on this AD action by March 10, 2006. Affected ADs (b) None. Applicability (c) This AD applies to all Aerospatiale Model ATR42–200, –300, –320, and –500 airplanes, certificated in any category. Unsafe Condition (d) This AD results from a report of cracking on the upper skin and ribs of the outer wing box on an in-service airplane. We are issuing this AD to detect and correct discrepancies (e.g., cracking, loose/sheared fasteners, distortion) of the upper skin and rib feet of the outer wing boxes, which could result in reduced structural integrity of the airplane. rmajette on PROD1PC67 with PROPOSALS1 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. External Inspection and Repair (f) Before the accumulation of 4,000 total flight cycles, or within 3 months after the effective date of this AD, whichever is later: Do an external detailed inspection for discrepancies of the upper skin panels of the outer wing box on the left and right wing, from rib 24 to rib 29. Do the inspection in accordance with Part A of the Accomplishment Instructions of Avions de Transport Regional Service Bulletin ATR42– 57–0064, dated December 16, 2004. (1) If any discrepancy is found: Before further flight, do the actions in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD. VerDate Aug<31>2005 19:58 Feb 07, 2006 Jkt 208001 (i) Repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, ´ ´ FAA; or the Direction Geenerale de l’Aviation Civile (DGAC) (or its delegated agent). (ii) Do the internal inspection in accordance with paragraph (g) of this AD. (2) If no discrepancy is found: Within 4 months after doing the external detailed inspection, do the internal inspection in accordance with paragraph (g) of this AD. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ (g) At the applicable time specified in paragraph (f)(1)(ii) or (f)(2) of this AD: Inspect for discrepancies of the rib feet from rib 24 to rib 29 using one of the inspection methods specified in paragraph (g)(1) or (g)(2) of this AD. Do the inspection in accordance with Part B of the Accomplishment Instructions of Avions de Transport Regional Service Bulletin ATR42–57–0064, dated December 16, 2004. If any discrepancy is found during any inspection required by this paragraph: Before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent). (1) A borescopic inspection through access doors. (2) A detailed inspection after removing the leading edge of the wing. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (i) French airworthiness directive F–2004– 191, dated December 22, 2004, also addresses the subject of this AD. Issued in Renton, Washington, on January 30, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–1685 Filed 2–7–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 6415 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23818; Directorate Identifier 2005–NM–228–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767 Airplanes Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking. AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This proposed AD would require repetitive measurements of the rudder and elevator freeplay, repetitive lubrication of rudder and elevator components, and related investigative/corrective actions if necessary. This proposed AD results from reports of freeplay-induced vibration of the rudder and the elevator. 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 excessive vibration of the airframe during flight, which could result in loss of control of the airplane. DATES: We must receive comments on this proposed AD by March 27, 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, E:\FR\FM\08FEP1.SGM 08FEP1 6416 Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules the AD docket shortly after the Docket Management System receives them. 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6450; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion 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–2006–23818; Directorate Identifier 2005–NM–228–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 We have received reports of freeplayinduced vibration of the rudder and the elevator on Model 767 airplanes. Excessive corrosion and wear of components and/or interfaces allow 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. When divergent flutter occurs, the amplitude of each cycle or oscillation is larger than the last one and the surface can quickly reach its structural load limits. Excessive vibration of the airframe, if not corrected, could result in loss of control of the airplane. Relevant Service Information We have reviewed Boeing Special Attention Service Bulletin 767–27– 0197, dated October 27, 2005 (for Model 767–200, –300, and –300F series airplanes); and Boeing Special Attention Service Bulletin 767–27–0198, dated October 27, 2005 (for Model 767–400ER series airplanes). The service bulletins describe procedures for repetitive measurements of the rudder freeplay and the elevator freeplay for each of the three power control actuators (PCAs) that move the rudder and elevator. If the freeplay exceeds certain specified limits, the service bulletins describe procedures for doing applicable related investigative and corrective actions. Related investigative actions include doing a general visual inspection for wear of the affected components such as the rudder and elevator hinge bolts, bearings, and bushings; elevator and rudder hinges; and hinge bearings, reaction links, hanger link bearings, and rod end assemblies. Corrective actions include repairing or replacing the affected part if necessary and repeating the freeplay measurement and any related investigative and corrective actions until the maximum freeplay is within acceptable limits. The service bulletins also describe procedures for repetitive lubrication of the rudder and elevator components such as the rudder and elevator hinges; and rudder and elevator PCA reaction links, hanger links, and rod end assemblies. The service bulletins note that, if the freeplay measurement and a lubrication cycle are due at the same time, the freeplay measurement must be completed before the lubrication. The repetitive interval for the lubrication varies depending on the type of grease used. 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, except as discussed under ‘‘Difference Between the Proposed AD and the Service Bulletins.’’ Difference Between the Proposed AD and the Service Bulletins Operators should note that, although the Accomplishment Instructions of the referenced service bulletins describe procedures for submitting inspections results to the manufacturer, this proposed AD would not require that action. Costs of Compliance There are about 979 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. No parts are necessary to accomplish either action. ESTIMATED COSTS Average labor rate per hour $ Work hours Action Cost per airplane $ Number of U.S.-registered airplanes rmajette on PROD1PC67 with PROPOSALS1 Freeplay measurement ............. 8 65 520, per measurement cycle .... 423 Lubrication ................................. 27 65 1,755, per lubrication cycle ....... 423 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Aug<31>2005 15:24 Feb 07, 2006 Jkt 208001 rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 Fleet cost $ 219,960, per measurement cycle. 42,365, per lubrication cycle. Aviation Programs, describes in more detail the scope of the Agency’s authority. E:\FR\FM\08FEP1.SGM 08FEP1 Federal Register / Vol. 71, No. 26 / Wednesday, February 8, 2006 / Proposed Rules 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: rmajette on PROD1PC67 with PROPOSALS1 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2006–23818; Directorate Identifier 2005–NM–228–AD. VerDate Aug<31>2005 15:24 Feb 07, 2006 Jkt 208001 Comments Due Date (a) The FAA must receive comments on this AD action by March 27, 2006. Affected ADs (b) None Applicability (c) This AD applies to all Boeing Model 767–200, –300, –300F, and –400ER series airplanes, certificated in any category. Unsafe Condition (d) This AD results from reports of freeplay-induced vibration of the rudder and the elevator. 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 excessive vibration of the airframe during flight, which could result in 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. Service Bulletin References (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of the following service bulletins, as applicable: (1) For Model 767–200, –300, and –300F series airplanes: Boeing Special Attention Service Bulletin 767–27–0197, dated October 27, 2005; and (2) For Model 767–400ER series airplanes: Boeing Special Attention Service Bulletin 767–27–0198, dated October 27, 2005. Repetitive Measurements (g) Within 18 months after the effective date of this AD: Measure the rudder and elevator freeplay. Repeat the measurement thereafter at intervals not to exceed 12,000 flight hours or 36 months, whichever occurs first. Do all actions required by this paragraph in accordance with the applicable service bulletin. Related Investigative and Corrective Actions (h) If any measurement found in paragraph (g) of this AD exceeds any applicable limit specified in the service bulletin: Before further flight, do the applicable related investigative and corrective actions in accordance with the applicable service bulletin. Repetitive Lubrication (i) Within 9 months after the effective date of this AD: Lubricate the rudder and elevator components specified in the service bulletin. Repeat the lubrication thereafter at the applicable interval in paragraph (i)(1) or (i)(2) of this AD. Do all actions required by this paragraph in accordance with the applicable service bulletin. (1) For airplanes on which BMS 3–33 grease is not used: At intervals not to exceed 3,000 flight hours or 9 months, whichever occurs first. (2) For airplanes on which BMS 3–33 grease is used: At intervals not to exceed PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 6417 6,000 flight hours or 18 months, whichever occurs first. Concurrent Repetitive Cycles (j) If a freeplay measurement required by paragraph (g) of this AD and a lubrication cycle required by paragraph (i) of this AD are due at the same time or will be accomplished during the same maintenance visit, the freeplay measurement and applicable related investigative and corrective actions must be done before the lubrication is accomplished. No Reporting Required (k) Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (l)(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 § 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 January 30, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–1686 Filed 2–7–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23815; Directorate Identifier 2005–NM–222–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737 Airplanes Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking. AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 737 airplanes. This proposed AD would require repetitive measurement of the freeplay of both E:\FR\FM\08FEP1.SGM 08FEP1

Agencies

[Federal Register Volume 71, Number 26 (Wednesday, February 8, 2006)]
[Proposed Rules]
[Pages 6415-6417]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-1686]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23818; Directorate Identifier 2005-NM-228-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking.

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Boeing Model 767 airplanes. This proposed AD would require 
repetitive measurements of the rudder and elevator freeplay, repetitive 
lubrication of rudder and elevator components, and related 
investigative/corrective actions if necessary. This proposed AD results 
from reports of freeplay-induced vibration of the rudder and the 
elevator. 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 excessive 
vibration of the airframe during flight, which could result in loss of 
control of the airplane.

DATES: We must receive comments on this proposed AD by March 27, 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,

[[Page 6416]]

1601 Lind Avenue, SW., Renton, Washington 98055-4056; 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-
23818; Directorate Identifier 2005-NM-228-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 the 
rudder and the elevator on Model 767 airplanes. Excessive corrosion and 
wear of components and/or interfaces allow 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. When divergent flutter 
occurs, the amplitude of each cycle or oscillation is larger than the 
last one and the surface can quickly reach its structural load limits. 
Excessive vibration of the airframe, if not corrected, could result in 
loss of control of the airplane.

Relevant Service Information

    We have reviewed Boeing Special Attention Service Bulletin 767-27-
0197, dated October 27, 2005 (for Model 767-200, -300, and -300F series 
airplanes); and Boeing Special Attention Service Bulletin 767-27-0198, 
dated October 27, 2005 (for Model 767-400ER series airplanes). The 
service bulletins describe procedures for repetitive measurements of 
the rudder freeplay and the elevator freeplay for each of the three 
power control actuators (PCAs) that move the rudder and elevator. If 
the freeplay exceeds certain specified limits, the service bulletins 
describe procedures for doing applicable related investigative and 
corrective actions. Related investigative actions include doing a 
general visual inspection for wear of the affected components such as 
the rudder and elevator hinge bolts, bearings, and bushings; elevator 
and rudder hinges; and hinge bearings, reaction links, hanger link 
bearings, and rod end assemblies. Corrective actions include repairing 
or replacing the affected part if necessary and repeating the freeplay 
measurement and any related investigative and corrective actions until 
the maximum freeplay is within acceptable limits. The service bulletins 
also describe procedures for repetitive lubrication of the rudder and 
elevator components such as the rudder and elevator hinges; and rudder 
and elevator PCA reaction links, hanger links, and rod end assemblies. 
The service bulletins note that, if the freeplay measurement and a 
lubrication cycle are due at the same time, the freeplay measurement 
must be completed before the lubrication. The repetitive interval for 
the lubrication varies depending on the type of grease used. 
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, except as discussed under 
``Difference Between the Proposed AD and the Service Bulletins.''

Difference Between the Proposed AD and the Service Bulletins

    Operators should note that, although the Accomplishment 
Instructions of the referenced service bulletins describe procedures 
for submitting inspections results to the manufacturer, this proposed 
AD would not require that action.

Costs of Compliance

    There are about 979 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. No parts are necessary 
to accomplish either action.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of
                                                 Average     Cost per airplane      U.S.-
             Action               Work  hours   labor rate           $            registered     Fleet cost  $
                                               per  hour $                        airplanes
----------------------------------------------------------------------------------------------------------------
Freeplay measurement............            8           65  520, per                     423  219,960, per
                                                             measurement cycle.                measurement
                                                                                               cycle.
Lubrication.....................           27           65  1,755, per                   423  42,365, per
                                                             lubrication cycle.                lubrication
                                                                                               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.

[[Page 6417]]

    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-2006-23818; Directorate Identifier 2005-NM-
228-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by March 27, 
2006.

Affected ADs

    (b) None

Applicability

    (c) This AD applies to all Boeing Model 767-200, -300, -300F, 
and -400ER series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from reports of freeplay-induced vibration 
of the rudder and the elevator. 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 excessive vibration of the airframe during flight, 
which could result in 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.

Service Bulletin References

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of the following service bulletins, as 
applicable:
    (1) For Model 767-200, -300, and -300F series airplanes: Boeing 
Special Attention Service Bulletin 767-27-0197, dated October 27, 
2005; and
    (2) For Model 767-400ER series airplanes: Boeing Special 
Attention Service Bulletin 767-27-0198, dated October 27, 2005.

Repetitive Measurements

    (g) Within 18 months after the effective date of this AD: 
Measure the rudder and elevator freeplay. Repeat the measurement 
thereafter at intervals not to exceed 12,000 flight hours or 36 
months, whichever occurs first. Do all actions required by this 
paragraph in accordance with the applicable service bulletin.

Related Investigative and Corrective Actions

    (h) If any measurement found in paragraph (g) of this AD exceeds 
any applicable limit specified in the service bulletin: Before 
further flight, do the applicable related investigative and 
corrective actions in accordance with the applicable service 
bulletin.

Repetitive Lubrication

    (i) Within 9 months after the effective date of this AD: 
Lubricate the rudder and elevator components specified in the 
service bulletin. Repeat the lubrication thereafter at the 
applicable interval in paragraph (i)(1) or (i)(2) of this AD. Do all 
actions required by this paragraph in accordance with the applicable 
service bulletin.
    (1) For airplanes on which BMS 3-33 grease is not used: At 
intervals not to exceed 3,000 flight hours or 9 months, whichever 
occurs first.
    (2) For airplanes on which BMS 3-33 grease is used: At intervals 
not to exceed 6,000 flight hours or 18 months, whichever occurs 
first.

Concurrent Repetitive Cycles

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

No Reporting Required

    (k) Although the service bulletins referenced in this AD specify 
to submit certain information to the manufacturer, this AD does not 
include that requirement.

Alternative Methods of Compliance (AMOCs)

    (l)(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 January 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-1686 Filed 2-7-06; 8:45 am]
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