[Federal Register Volume 70, Number 119 (Wednesday, June 22, 2005)]
[Proposed Rules]
[Pages 36070-36072]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-12299]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21594; Directorate Identifier 2005-NM-067-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10 and 
DC-10-10F Airplanes; Model DC-10-15 Airplanes; Model DC-10-30 and DC-
10-30F (KC-10A and KDC-10) Airplanes; Model DC-10-40 and DC-10-40F 
Airplanes; Model MD-10-10F and MD-10-30F Airplanes; and Model MD-11 and 
MD-11F 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 McDonnell Douglas transport category airplanes. This 
proposed AD would require an inspection of the torque tube assembly for 
the rudder pedal for cracking; an inspection of the torque tube 
assembly to determine the thickness of the torque tube wall, if 
necessary; and replacing the rudder torque tube with a new or 
serviceable rudder torque tube, if necessary. This proposed AD is 
prompted by a report of a broken rudder pedal torque tube. We are 
proposing this AD to prevent failure of a rudder pedal torque tube, 
which could result in loss of rudder control and nose wheel steering 
controlled by the rudder pedal, and consequent reduced controllability 
of the airplane.

DATES: We must receive comments on this proposed AD by August 8, 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, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024).
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person 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. This docket 
number is FAA-2005-21594; the directorate identifier for this docket is 
2005-NM-067-AD.

[[Page 36071]]


FOR FURTHER INFORMATION CONTACT: Ron Atmur, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5224; fax (562) 627-5210.

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 under ADDRESSES. Include ``Docket No. FAA-2005-21594; 
Directorate Identifier 2005-NM-067-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.

Examining the Docket

    You can 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 
(DMS) receives them.

Discussion

    We have received a report indicating that an operator found a 
broken rudder pedal torque tube on a McDonnell Douglas MD-11 airplane, 
after hearing a loud bang and the sound of cracking metal before losing 
rudder input during a pre-flight check. The airplane had accumulated 
3,313 landing cycles and 18,416 flight hours. Analysis by the operator 
and airplane manufacturer revealed that the wall thickness of the 
torque tube for the rudder pedal was below the minimum specifications 
at the point of failure. A thin wall and the existence of a weld 
applied to the outside surface of the wall during manufacture of the 
torque tube contributed to its failure. Failure of a rudder pedal 
torque tube could result in loss of rudder control and nose wheel 
steering controlled by the rudder pedal, and consequent reduced 
controllability of the airplane.
    The torque tube assembly for the rudder pedals on certain Model MD-
11 airplanes is identical to those on the affected Model DC-10-10 and 
DC-10-10F airplanes; Model DC-10-15 airplanes; Model DC-10-30 and DC-
10-30F (KC-10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F 
airplanes; Model MD-10-10F and MD-10-30F airplanes; and MD-11F 
airplanes. Therefore, all of these models may be subject to the same 
unsafe condition.

Relevant Service Information

    We have reviewed the following Boeing Alert Service Bulletins:
     DC10-27A236, including Appendix A and Appendix B, dated 
February 17, 2005, for McDonnell Douglas Model DC-10-10 and DC-10-10F 
airplanes; Model DC-10-15 airplanes; Model DC-10-30 and DC-10-30F (KC-
10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F airplanes; and 
Model MD-10-10F and MD-10-30F airplanes; and
     MD11-27A083, including Appendix A and Appendix B, dated 
February 17, 2005, for McDonnell Douglas Model MD-11 and MD-11F 
airplanes.
    The service bulletins describe the following procedures:
     Doing a special detailed eddy current inspection of the 
torque tube assembly for the rudder pedal for cracking.
     If no cracking is found, doing a special detailed 
ultrasonic inspection of the torque tube assembly to determine the wall 
thickness of the torque tube.
     If any cracking is found or if the wall thickness of the 
torque tube is below certain limits specified in Appendix B of the 
service bulletin, replacing the torque tube with a new or serviceable 
torque tube.
    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. Therefore, we are proposing this AD, which 
would require accomplishing the actions specified in the service 
information described previously.

Costs of Compliance

    There are about 960 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 366 airplanes of 
U.S. registry. The proposed inspection would take about 16 work hours 
per airplane, at an average labor rate of $65 per work hour. Based on 
these figures, the estimated cost of the proposed AD for U.S. operators 
is $380,640, or $1,040 per airplane.
    For Model DC-10-10 and DC-10-10F airplanes; Model DC-10-15 
airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes; 
Model DC-10-40 and DC-10-40F airplanes; and Model MD-10-10F and MD-10-
30F airplanes: The proposed replacement if necessary would take about 
16 work hours per airplane, at an average labor rate of $65 per work 
hour. Required parts would cost about $12,892 per airplane. Based on 
these figures, the estimated cost of the proposed replacements is 
$13,932 per airplane.
    For Model MD-11 and MD-11F airplanes: The proposed replacement if 
necessary would take about 5 work hours per airplane, at an average 
labor rate of $65 per work hour. Required parts would cost about 
$12,892 per airplane. Based on these figures, the estimated cost of the 
proposed replacements is $13,217 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

[[Page 36072]]

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

McDonnell Douglas: Docket No. FAA-2005-21594; Directorate Identifier 
2005-NM-067-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this AD action by August 8, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the airplanes identified in Table 1 of 
this AD; certificated in any category.

                         Table 1--Applicability
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          McDonnell Douglas--                   As identified in--
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Model DC-10-10 and DC-10-10F airplanes;  Boeing Alert Service Bulletin
 Model DC-10-15 airplanes; Model DC-10-   DC10-27A236, dated February
 30 and DC-10-30F (KC-10A and KDC-10)     17, 2005.
 airplanes; Model DC-10-40 and DC-10-
 40F airplanes; and Model MD-10-10F and
 MD-10-30F airplanes.
----------------------------------------
Model MD-11 and MD-11F airplanes.......  Boeing Alert Service Bulletin
                                          MD11-27A083, dated February
                                          17, 2005.
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Unsafe Condition

    (d) This AD was prompted by a report of a broken rudder pedal 
torque tube. We are issuing this AD to prevent failure of a rudder 
pedal torque tube, which could result in loss of rudder control and 
nose wheel steering controlled by the rudder pedal, and consequent 
reduced controllability 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.

Eddy Current Inspection and Replacement if Necessary

    (f) Within 6 months after the effective date of this AD, do a 
special detailed eddy current inspection of the torque tube assembly 
for the rudder pedal for cracks, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin DC10-
27A236, including Appendix A and Appendix B, dated February 17, 
2005; or Boeing Alert Service Bulletin MD11-27A083, including 
Appendix A and Appendix B, dated February 17, 2005; as applicable. 
If any crack is found, before further flight, replace the rudder 
pedal torque tube with a new or serviceable rudder pedal torque 
tube, in accordance with the applicable service bulletin.

Ultrasonic Inspection and Replacement, if Necessary

    (g) If no cracking is found during the special detailed eddy 
current inspection required by paragraph (f) of this AD, before 
further flight, do a special detailed ultrasonic inspection of the 
torque tube assembly for the rudder pedal to determine the wall 
thickness of the rudder pedal torque tube, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin DC10-
27A236, including Appendix A and Appendix B, dated February 17, 
2005; or Boeing Alert Service Bulletin MD11-27A083, including 
Appendix A and Appendix B, dated February 17, 2005; as applicable.
    (1) If the wall thickness of the torque tube is within the 
limits identified as area C in Appendix B of the applicable service 
bulletin, no further action is required by this AD.
    (2) If the wall thickness of the torque tube is within the 
limits identified as area B in Appendix B of the applicable service 
bulletin, within 6,000 flight hours after doing the special detailed 
ultrasonic inspection, replace the torque tube with a new or 
serviceable torque tube, in accordance with the applicable service 
bulletin.
    (3) If the wall thickness of the torque tube is below the 
minimum limits, which are identified as area A in Appendix B of the 
applicable service bulletin, before further flight, replace the 
torque tube with a new or serviceable torque tube, in accordance 
with the applicable service bulletin.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Los Angeles 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) 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 Delegation Option 
Authorization Organization who has been authorized by the Manager, 
Los Angeles 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 June 14, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-12299 Filed 6-21-05; 8:45 am]
BILLING CODE 4910-13-P