[Federal Register: June 22, 2005 (Volume 70, Number 119)]

[Proposed Rules]               

[Page 36070-36072]

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

[DOCID:fr22jn05-35]                         

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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 a one time inspection of the Rudder Pedal
torque tube assembly for minimum wall thickness and existing cracks to
determine the condition of the part. the rudder pedal for cracking. An
inspection of the torque tube assembly to determine the thickness of the
torque tube wall if necessary and, if necessary, replacing the rudder
torque tube with a new or serviceable Rudder Pedal torque tube will
insure the integrity of the system. 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
partial 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  HYPERLINK
"http://frwebgate.access.gpo.gov/cgi-bin/leaving.cgi?from=leavingFR.html
&log=linklog&to=http://dms.dot.gov" http://dms.dot.gov  and follow 

the instructions for sending your comments electronically.

     Government-wide rulemaking Web site: Go to  HYPERLINK
"http://frwebgate.access.gpo.gov/cgi-bin/leaving.cgi?from=leavingFR.html
&log=linklog&to=http://www.regulations.gov" 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 

 HYPERLINK
"http://frwebgate.access.gpo.gov/cgi-bin/leaving.cgi?from=leavingFR.html
&log=linklog&to=http://dms.dot.gov" 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  HYPERLINK
"http://frwebgate.access.gpo.gov/cgi-bin/leaving.cgi?from=leavingFR.html
&log=linklog&to=http://dms.dot.gov" 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 
HYPERLINK
"http://frwebgate.access.gpo.gov/cgi-bin/leaving.cgi?from=leavingFR.html
&log=linklog&to=http://dms.dot.gov" http://dms.dot.gov .

Examining the Docket

    You can examine the AD docket on the Internet at  HYPERLINK
"http://frwebgate.access.gpo.gov/cgi-bin/leaving.cgi?from=leavingFR.html
&log=linklog&to=http://dms.dot.gov" 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 partial 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 existing cracks the rudder pedal for cracking.

     If no cracks ing is are found, doing a special detailed 

ultrasonic inspection of the torque tube assembly to determine the wall 

thickness of the torque tube.

     If any cracks are found or if the wall thickness of the 

torque tube is below certain limits specified in Appendix B of the 

service bulletin, replacement of the torque tube with a new or
serviceable 

torque tube is required .

    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 96 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
$19,132 13,932 per airplane.

    For Model MD-11 and MD-11F airplanes: The proposed replacement if
necessary would take about 18 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 $14,062 13,217 per airplane.

Reasons(s) for Proposed Text/Comments: 

The NPRM underestimates the number of work hours required to replace the
rudder pedal torque tube.  The Boeing Service Bulletins(SBs) show a
higher number of task hours for replacement of the rudder pedal torque
tube.  The SBs include estimates for time to gain access, remove and
replace torque tube, adjust (for MD-11), and close access.  The DC-10
requires about 96 task hours total, versus 16 shown in the NPRM.  The
MD-11 requires about 18 task hours, versus 5 shown in the NPRM.

Name: Jack Evans                                            Group: OOP
Design Office



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 inspections required
by this 

AD performed within 6 months after the effective date of this AD,  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 existing 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

Reasons(s) for Proposed Text/Comments: 

The revised text accurately defines Boeing's intent and uses wording
consistent with the Boeing Alert Service Bulletins, DC10-27A236 &
MD11-27A083. These changes will eliminate potential confusion by the
airline operators between the FAA AD & Boeing Alert S/B's. (Added or
revised sentences are underlined for clarification.)

Name: Greg Fukaye / Jim Talay              Group:  Hydro- Mechanical



