Airworthiness directives: Boeing,

[Federal Register: October 7, 2005 (Volume 70, Number 194)]

[Proposed Rules]

[Page 58620-58623]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr07oc05-13]

Proposed Rules Federal Register

This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules.

[[Page 58620]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22623; Directorate Identifier 2004-NM-80-AD]

RIN 2120-AA64

Airworthiness Directives; Boeing Model 767 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This proposed AD would require the following actions for the drive mechanism of the horizontal stabilizer: Repetitive detailed inspections for discrepancies and loose ball bearings; repetitive lubrication of the ballnut and ballscrew; repetitive measurements of the freeplay between the ballnut and the ballscrew; and corrective action if necessary. This proposed AD is prompted by a report of extensive corrosion of a ballscrew in the drive mechanism of the horizontal stabilizer on a similar airplane model. We are proposing this AD to prevent an undetected failure of the primary load path for the ballscrew in the horizontal stabilizer and subsequent wear and failure of the secondary load path, which could lead to loss of control of the horizontal stabilizer and consequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by November 21, 2005.

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.

By 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.

For service information identified in this proposed AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124- 2207.

You can examine the contents of this AD docket on the Internet at http://dms.dot.gov, or at the Docket Management Facility, U.S.

Department of Transportation, 400 Seventh Street SW., Room PL-401, on the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Kelly McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Airplane Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055- 4056; telephone (425) 917-6490; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

The FAA has implemented new procedures for maintaining AD dockets electronically. As of May 17, 2004, new AD actions are posted on DMS and assigned a docket number. We track each action and assign a corresponding directorate identifier. The DMS AD docket number is in the form ``Docket No. FAA-2005-99999.'' The Transport Airplane Directorate identifier is in the form ``Directorate Identifier 2005-NM- 999-AD.'' Each DMS AD docket also lists the directorate identifier (``Old Docket Number'') as a cross-reference for searching purposes.

Comments Invited

We invite you to submit any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ``Docket No. FAA-2005-22623; Directorate Identifier 2004-NM-80-AD'' in the subject line 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 submitted 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 can review DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you can visit http://dms.dot.gov.

We are reviewing the writing style we currently use in regulatory documents. We are interested in your comments on whether the style of this document is clear, and your suggestions to improve the clarity of our communications that affect you. You can get more information about plain language at http://www.faa.gov/language and http://www .plainlanguage.gov.

Examining the Docket

You can examine the AD docket 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 DMS receives them.

Discussion

On January 31, 2000, there was an accident involving a McDonnell Douglas Model DC-9-83 (MD-83) airplane. The National Transportation Safety Board (NTSB) determined that the probable cause of this accident was a loss of airplane pitch control resulting from the in-flight failure of the acme nut threads of the jackscrew assembly of the horizontal stabilizer trim system. The NTSB concluded that the thread failure was caused by excessive wear, resulting from insufficient lubrication of the jackscrew assembly.

[[Page 58621]]

The drive mechanism of the horizontal stabilizer on McDonnell Douglas Model DC-9-83 (MD-83) airplanes has a jackscrew assembly with an acme screw. The drive mechanism of the horizontal stabilizer on Boeing Model 767 airplanes uses a ballscrew. Acme screws and ballscrews have some differences in design, but perform similar functions and have the same airplane level effect following failure. The manufacturer's safety analysis of the 767 drive mechanism found no safety problems with the configuration of the drive mechanism, but showed that changes to the maintenance procedures and maintenance intervals are required to keep the drive mechanism properly maintained and operating as designed.

We have received a report indicating that the ballscrew in the drive mechanism of the horizontal stabilizer on a Boeing Model 757 series airplane showed extensive corrosion, which could lead to excessive wear. The ballscrew on Boeing Model 757 airplanes is similar to that on Boeing Model 767 airplanes that are the subject of this proposed AD. Therefore, both of these airplane models could have the same unsafe condition. We are considering separate action for the Boeing Model 757 series airplanes and other similar Boeing airplanes.

Extensive corrosion of the ballscrew in the drive mechanism of the horizontal stabilizer, if not corrected, could cause an undetected failure of the primary load path for the ballscrew and subsequent wear and failure of the secondary load path, which could lead to loss of control of the horizontal stabilizer and consequent loss of control of the airplane.

Relevant Service Information

We have reviewed the following service bulletins:

Boeing Service Bulletin 767-27A0194, Revision 1, dated July 21, 2005 (for Model 767-200, -300, and -300F series airplanes); and

Boeing Service Bulletin 767-27A0195, Revision 1, dated July 21, 2005 (for Model 767-400ER series airplanes).

The compliance times specified in the service bulletins are as follows:

For all airplanes: The compliance time for the initial detailed inspections and lubrication of the ballnut and ballscrew is 15,000 total flight hours or 18 months after the original issue date on the service bulletin, whichever occurs later. The inspection is repeated at intervals not to exceed 3,500 flight hours or 24 months, whichever occurs first; the lubrication is repeated at intervals not to exceed 2,000 flight hours or 12 months, whichever occurs first.

For all airplanes except those on which an FAA-approved low utilization maintenance program is in effect: The compliance time for the initial ballscrew-to-ballnut freeplay inspection is 15,000 flight hours after accomplishing the last ballscrew-to-ballnut freeplay inspection or 18 months after the original issue date on the service bulletin, whichever occurs later. If the inspection has never been done, the compliance time for the initial inspection is 15,000 flight hours after the delivery date of the airplane or 18 months after the original issue date on the service bulletin, whichever occurs later. The inspection is repeated at intervals not to exceed 18,000 flight hours.

For all airplanes except those on which an FAA-approved low utilization maintenance program is in effect: The compliance time for the initial ballscrew-to-ballnut freeplay inspection is 60 months after accomplishing the last ballscrew-to-ballnut freeplay inspection. If the inspection has never been done, the compliance time for the initial inspection is within 60 months after the delivery date of the airplane. The inspection is repeated at intervals not to exceed 72 months.

The service bulletins also describe the procedures in the following table for the drive mechanism of the horizontal stabilizer:

Procedures Specified in Boeing Service Bulletins 767-27A0194 and 767- 27A0195

Work package

Repetitive actions

Corrective action

1. Accomplish detailed Replace the ballscrew inspections for

   actuator with a new or discrepancies

   overhauled actuator if (including cracks,

   any discrepancy is corrosion, damage, and found during any worn areas); and a

   inspection. detailed inspection for loose ball bearings of the external areas of the drive mechanism and areas below the drive mechanism. 2................... Lubricate the ballnut Not applicable. and ballscrew of the horizontal stabilizer drive mechanism. 3................... Measure the freeplay Replace the ballscrew between the ballnut and actuator with a new or ballscrew.

   overhauled actuator if the freeplay is more than the specified limit.

   We have also reviewed Boeing Alert Service Bulletin 767-27A0185, dated July 10, 2003, which is included as an additional source of service information for accomplishing certain actions. This service bulletin applies to Boeing Model 767 airplanes that have line numbers 002 through 175 inclusive, and has procedures that are equivalent to those in Service Bulletins 767-27A0194 and 767-27A0195. Accomplishing the inspection and lubrication specified in Service Bulletin 767- 27A0185 is considered acceptable for compliance with the initial inspection and lubrication specified in Revision 1 of Boeing Service Bulletins 767-27A0194 and 767-27A0195.

   We have determined that accomplishing the actions specified in Revision 1 of Boeing Service Bulletins 767-27A0194 and 767-27A0195 will adequately address the unsafe condition.

   Revision 1 of Boeing Service Bulletins 767-27A0194 and 767-27A0195 refers to the 767 Airplane Maintenance Manuals (AMM) in the following table as additional sources of service information for accomplishing the detailed inspections, lubrications, freeplay measurements, and corrective action.

   Additional Sources of Service Information

   Boeing AMM

   Subject

   767-200.................................................

   27-41-10 767-200.................................................

   12-21-05

   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. Therefore, we are proposing this AD, which would require

   [[Page 58622]]

   the following actions for the drive mechanism of the horizontal stabilizer:

   Repetitive detailed inspections for discrepancies of the ballscrew assembly;

   Repetitive lubrication of the ballnut and ballscrew;

   Repetitive measurements of freeplay between the ballnut and the ballscrew; and

   Corrective action if necessary.

   The proposed AD would require you to use Revision 1 of Service Bulletins 767-27A0194 and 767-27A0195 to perform these actions; except as discussed under ``Difference Between the Proposed AD and Service Information.''

   Differences Between the Proposed AD and Service Information

   The service bulletins specify compliance times relative to the date of issuance of the service bulletins; however, this proposed AD would require compliance before the specified compliance time after the effective date of this AD.

   Costs of Compliance

   There are about 903 Model 767 airplanes in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this proposed AD, per cycle.

   Estimated Costs

   Number of U.S.- Repetitive actions

   Work Average labor

   Parts

   Cost per registered Fleet cost hours rate per hour

   airplane

   airplanes

   Detailed inspection..........................

   1

   $65 None............................

   $65

   411

   $26,715 Lubrication..................................

   1

   65 None............................

   65

   411

   26,715 Freeplay measurement.........................

   3

   65 None............................

   195

   411

   80,145

   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 will not have federalism implications under Executive Order 13132. This proposed AD will 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. See the ADDRESSES section for a location to examine the regulatory evaluation.

   List of Subjects in 14 CFR Part 39

   Air transportation, Airplane, 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 FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD):

   Boeing: Docket No. FAA-2005-22623; Directorate Identifier 2004-NM- 80-AD.

   Comments Due Date

   (a) The Federal Aviation Administration (FAA) must receive comments on this AD action by November 21, 2005.

   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 was prompted by a report of extensive corrosion of a ballscrew in the horizontal stabilizer of a similar airplane model. We are issuing this AD to prevent an undetected failure of the primary load path for the ballscrew in the drive mechanism of the horizontal stabilizer and subsequent wear and failure of the secondary load path, which could lead to loss of control of the horizontal stabilizer and consequent 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.

   Repetitive Detailed Inspections/Lubrications/Freeplay Measurement/ Corrective Action

   (f) Do all the applicable actions, including any applicable corrective action, specified in Work Packages 1, 2, and 3 of the Accomplishment Instructions of Boeing Service Bulletin 767-27A0194 (for Model 767-200, -300, and -300F series airplanes) or Boeing Service Bulletin 767-27A0195 (for Model 767-400ER series airplanes), both Revision 1, both dated July 21, 2005; as applicable. Do the actions at the applicable compliance time specified in Table 1 of paragraph 1.E. ``Compliance'' of the service bulletins; except, where the service bulletins specify a compliance time relative to the original issue date of the service bulletin, this AD requires compliance relative to the effective date of this AD. Where the service bulletins specify a compliance time relative to the delivery date of the airplane, this AD requires compliance relative to the date of issuance of the original standard airworthiness certificate. Do any applicable corrective action before further flight. Repeat the actions at the applicable repeat interval specified in Table 1 of paragraph 1.E ``Compliance'' of the service bulletins.

   Previously Accomplished Actions

   (g) For airplanes on which the drive mechanism of the horizontal stabilizer was replaced before the effective date of this AD with a drive mechanism that was not new or overhauled, and the detailed and freeplay inspections were not accomplished in

   [[Page 58623]]

   accordance with Boeing Alert Service Bulletin 767-27A0194 or 767- 27A0195, both dated August 21, 2003, as applicable: Within 4,000 flight hours or 24 months after the effective date of this AD, whichever is first, accomplish the inspections and perform any applicable corrective action before further flight in accordance with Work Package 3 of the Accomplishment Instructions of Boeing Service Bulletin 767-27A0194 or Boeing Service Bulletin 767-27A0195, both Revision 1, both dated July 21, 2005; as applicable.

   (h) For Model 767 airplanes that have line numbers 002 through 175 inclusive: Accomplishing the initial inspection, applicable corrective action, and lubrication before the effective date of this AD in accordance with Boeing Alert Service Bulletin 767-27A0185, dated July 10, 2003; is considered acceptable for compliance with the applicable actions required by paragraph (f) of this AD.

   Note 1: Boeing Service Bulletins 767-27A0194 and 767-27A0195, both Revision 1, both dated July 21, 2005, refer to the 767 Airplane Maintenance Manuals (AMM) in Table 1 of this AD as additional sources of service information for accomplishing the detailed inspections, lubrications, freeplay measurements, and corrective action.

   Table 1.--Additional Sources of Service Information

   Boeing AMM

   Subject

   767-200.................................................

   27-41-10 767-200.................................................

   12-21-05

   Parts Installation

   (i) As of the effective date of this AD, no person may install on any airplane a horizontal stabilizer trim actuator unless it is new or has been overhauled in accordance with Boeing Service Bulletins 767-27A0194 and 767-27A0195, both Revision 1, both dated July 21, 2005; or has been inspected, lubricated, and measured in accordance with paragraph (f) of this AD.

   Alternative Methods of Compliance (AMOCs)

   (j) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

   Issued in Renton, Washington, on September 30, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Airplane Certification Service.

   [FR Doc. 05-20267 Filed 10-6-05; 8:45 am]

   BILLING CODE 4910-13-P