[Federal Register: July 12, 2002 (Volume 67, Number 134)]
[Rules and Regulations]               
[Page 46098-46100]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12jy02-3]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-108-AD; Amendment 39-12802; AD 2002-14-02]
RIN 2120-AA64

 
Airworthiness Directives; Boeing Model 767-300 Series Airplanes 
Equipped With Rolls Royce RB211-524H Series Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Boeing Model 767-300 series airplanes equipped 
with Rolls Royce RB211-524H series engines. This action requires re-
routing a certain wire bundle containing control wiring for the thrust 
reverser actuation system. This action is necessary to ensure that 
control wiring for the thrust reverser actuation system is adequately 
separated. Inadequately separated wiring could allow a single failure 
to result in uncommanded deployment of a thrust reverser and consequent 
reduced controllability of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective July 29, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 29, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before September 10, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-108-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
9-anm-iarcomment@faa.gov. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-108-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in this AD may be obtained from 
Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 
98124-2207. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Technical Information: Dan Kinney, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 227-2666; fax (425) 227-1181.
    Other Information: Judy Golder, Airworthiness Directive Technical 
Editor/Writer; telephone (425) 687-4241, fax (425) 227-1232. Questions 
or comments may also be sent via the Internet using the following 
address: judy.golder@faa.gov. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft 
Word 97 for Windows or ASCII text.

SUPPLEMENTARY INFORMATION: During inspections performed in the course 
of certificating Boeing Model 767-400ER series airplanes, the FAA 
discovered that control wiring for the thrust reverser actuation system 
brake was routed under the same clamps as wiring that controls the 
pressure regulating shut-off valve and the differential pressure valve 
of the thrust reverser system, as well as wiring of unrelated systems. 
Due to the criticality of an uncommanded deployment of a thrust 
reverser in flight, the thrust reverser

[[Page 46099]]

actuation system incorporates multiple independent systems to lock the 
thrust reverser in the ``stowed'' position. The intent is that, if one 
locking system fails, the other locking systems will continue to 
function, keeping the thrust reverser locked in the ``stowed'' 
position. However, inadequate separation of control wiring for the 
thrust reverser actuation system could allow a single failure to damage 
wiring for more than one locking system, which could result in an 
uncommanded deployment of a thrust reverser and consequent reduced 
controllability of the airplane.
    A subsequent review of wiring designs on other Model 767 series 
airplanes revealed that a condition similar to that described 
previously also exists on Model 767-300 series airplanes equipped with 
Rolls Royce RB211-524H series engines. Therefore, these airplanes are 
subject to the same unsafe condition.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Service Bulletin 767-78-
0085, dated November 8, 2001. That service bulletin describes 
procedures for re-routing wire bundle W518, which is located along the 
leading edge of the right wing from the outboard pressure seal to the 
wing/strut disconnect. The procedures include performing a functional 
test to verify proper operation of the thrust reverser actuation system 
following the re-routing of the wire bundle. Accomplishment of the 
actions specified in the service bulletin is intended to adequately 
address the identified unsafe condition.

Explanation of Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design that may be 
registered in the United States at some time in the future, this AD is 
being issued to ensure that control wiring for the thrust reverser 
actuation system is adequately separated. Inadequately separated wiring 
could allow a single failure to result in uncommanded deployment of a 
thrust reverser and consequent reduced controllability of the airplane. 
This AD requires accomplishment of the actions specified in the service 
bulletin described previously.

Cost Impact

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes included in the applicability of this rule 
currently are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
the FAA considers that this rule is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject airplanes 
are imported and placed on the U.S. Register in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 10 work hours to 
accomplish the required actions, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of this AD would be 
$600 per airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. Register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
rule by submitting such written data, views, or arguments as they may 
desire. Communications shall identify the Rules Docket number and be 
submitted in triplicate to the address specified under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the AD is 
being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-108-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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.

[[Page 46100]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-14-02  Boeing: Amendment 39-12802. Docket 2002-NM-108-AD.

    Applicability: Model 767-300 series airplanes, line numbers 001 
through 810 inclusive, certificated in any category, and equipped 
with Rolls Royce RB211-524H series engines.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To ensure that control wiring for the thrust reverser actuation 
system is adequately separated in order to prevent a single failure 
from resulting in uncommanded deployment of a thrust reverser and 
consequent reduced controllability of the airplane, accomplish the 
following:

Re-Routing of Wire Bundle and Functional Test

    (a) Within 36 months after the effective date of this AD, re-
route wire bundle W518 (which is located along the leading edge of 
the right wing from the outboard pressure seal to the wing/strut 
disconnect), according to Boeing Service Bulletin 767-78-0085, dated 
November 8, 2001. Before the next flight after the re-routing, the 
functional test specified in the procedures in the service bulletin 
must be successfully completed.

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (d) The actions shall be done in accordance with Boeing Service 
Bulletin 767-78-0085, dated November 8, 2001. This incorporation by 
reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, 
Seattle, Washington 98124-2207. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (e) This amendment becomes effective on July 29, 2002.

    Issued in Renton, Washington, on July 2, 2002.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-17244 Filed 7-11-02; 8:45 am]
BILLING CODE 4910-13-P