[Federal Register Volume 61, Number 138 (Wednesday, July 17, 1996)]
[Rules and Regulations]
[Pages 37202-37204]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-17982]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-161-AD; Amendment 39-9695; AD 96-14-51]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) T96-14-51 that was sent 
previously to all known U.S. owners and operators of Boeing Model 767 
series airplanes by individual telegrams. This AD requires an 
inspection of the aileron control cables and the generator feeder 
cables to detect chafing damage of the cables and to ensure that a 
minimum clearance exists between them. It also requires the correction 
of any discrepancies detected and submission of a report of inspection 
results to the FAA. This amendment is prompted by reports of failure of 
the aileron control cables due to inadequate clearance between the 
aileron control cable and the generator power feeder cable, which 
occurred during manufacture of the airplane.. The actions specified by 
this AD are intended to prevent reduced controllability of the airplane 
due to failure of the aileron control cable.

DATES: Effective July 22, 1996, to all persons except those persons to 
whom it was made immediately effective by telegraphic AD T96-14-51, 
issued July 3, 1996, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 22, 1996.
    Comments for inclusion in the Rules Docket must be received on or 
before September 16, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 96-NM-161-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The applicable service information 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: Stephen S. Oshiro, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Transport Airplane 
Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue, 
SW., Renton, Washington 98055-4056; telephone (206) 227-2793; fax (206) 
227-1181.

SUPPLEMENTARY INFORMATION: On July 3, 1996, the FAA issued telegraphic 
AD T96-14-51, which is applicable to certain Boeing Model 767 series 
airplanes. That action was prompted by two reports of failure of the 
aileron control cable on these airplanes. The failures have been 
attributed to inadequate clearance between the left side aileron 
control cable and the right generator power feeder cable, which 
occurred during manufacture of the airplane.
    One of the reported failures resulted in uncommanded movement of 
the left side ailerons shortly after takeoff, which required 
significant compensating control wheel input to correct, and resulted 
in an air turnback to the departure airport. The uncommanded aileron 
movement occurred almost concurrently with the right generator tripping 
off-line. Investigation revealed that the aileron control cable A2B-3 
was broken. Further investigation revealed that the right generator 
power feeder cable (W208) had been damaged (due to chafing) and 
approximately \1/4\-inch of the conductor was exposed. This cable is 
routed from the aft side of the P32 panel. The power feeder cable can 
chafe the aileron control cable (A2B-3) at approximately Station 340, 
Water Line (WL) 190, Right Buttock Line (RBL) 67.5. The airplane 
involved in this incident had accumulated 5,940 flight hours and 857 
flight cycles.
    The second reported failure occurred during a pre-flight control 
check of the airplane while it was on the ground. Investigation 
revealed that the left side aileron control cable was broken at the 
same approximate location as breakage found on the airplane involved in 
the previous incident. Additionally, the right generator power feeder 
cable was damaged.
    Contact between the generator power feeder cable and the aileron 
control cable on either the left or right side of the airplane could 
result in chafing damage to the insulation on the feeder cable. Such 
damage could cause short circuiting and arcing, which could sever the 
aileron control cable. This condition, if not corrected, could result 
in failure of the aileron control cable, and consequent reduced 
controllability of the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
767-24A0113, Revision 1, dated July 2, 1996, which describes procedures 
for a one-time inspection of the aileron control cable (A2B-3) and the 
right generator power feeder cable (W208) on the right side of the 
airplane, and the aileron control cable (A1A-3) and the left generator 
power feeder cable (W204) on the left side of the airplane. The intent 
of this inspection is to detect chafing damage of the cables, and to 
ensure that a minimum clearance of one inch exists between the power 
feeder cables and aileron control cables. The service bulletin also 
describes procedures for

[[Page 37203]]

repair or adjustment of the cables, if necessary.

Explanation of Requirements of the Rule

    Since the unsafe condition described is likely to exist or develop 
on other airplanes of the same type design, the FAA issued Telegraphic 
AD T96-14-51 to prevent reduced controllability of the airplane due to 
failure of the aileron control cable. The AD requires a one-time 
inspection of the aileron control cables and the generator power feeder 
cables on the left and right sides of the airplane to detect chafing 
damage of the cables, and to ensure that a minimum clearance of one 
inch exists between them. The AD also requires repair or adjustment of 
the cables, if necessary. These actions are required to be accomplished 
in accordance with the alert service bulletin previously described.
    This AD also requires that operators submit a report to the FAA of 
inspection findings where clearance is found to be less than one inch.

Publication and Effectivity of AD

     Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual telegrams 
issued on July 3, 1996, to all known U.S. owners and operators of 
Boeing Model 767 series airplanes. These conditions still exist, and 
the AD is hereby published in the Federal Register as an amendment to 
section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to 
make it effective to all persons.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an 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.
    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 96-NM-161-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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.


Sec. 39.13  [Amended]

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

96-14-51  Boeing: Amendment 39-9695. Docket 96-NM-161-AD.

    Applicability: Model 767 series airplanes; line numbers 1 
through 618 inclusive, except for line numbers 580, 590, 594, 598, 
and 600; certificated in any category.

    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 (c) 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 prevent reduced controllability of the airplane due to 
failure of the aileron control cable, accomplish the following:
    (a) Within 10 days after the effective date of this AD: Perform 
a one-time inspection of the aileron control cables and the 
generator feeder cables on both the left and right sides of the 
airplane to detect chafing damage of the cables, and to ensure that 
a minimum clearance of 1.0 inch exists between the power feeders and 
aileron control cables, in accordance with Boeing Alert Service 
Bulletin 767-24A0113, Revision 1, dated July 2, 1996.
    (1) If a minimum clearance of 1.0 inch exists between the 
cables, and if no damage is detected: No further action is required 
by this AD.
    (2) If the clearance between the cables is 0.5 inch or more, but 
less than 1.0 inch, and if no contact between the cables or damage 
of the cables is detected: Within 500 flight hours after the 
inspection, adjust the power feeder cable to achieve a minimum 
clearance of 1.0 inch from the respective aileron control cables, in 
accordance with the alert service bulletin.
    (3) If the clearance between the cables is less than 0.5 inch, 
or if any contact between the cables or damage of the cables is 
detected: Prior to further flight, repair the damage and adjust the 
cables to achieve a minimum clearance of 1.0 inch from the 
respective aileron control cables, in accordance with the alert 
service bulletin.

[[Page 37204]]

    (b) For any airplane on which damage of the aileron control 
cable or the generator feeder cable is observed, or for which 
clearance between the cables is less than 1 inch, as detected by the 
inspection required by paragraph (a) of this AD: Within 10 days 
after accomplishing the inspection, submit a report of inspection 
findings to the FAA, Manager, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; fax (206) 227-
1181. The report shall include the items identified in paragraphs 
(b)(1), (b)(2), (b)(3), and (b)(4) of this AD. Information 
collection requirements contained in this regulation have been 
approved by the Office of Management and Budget (OMB) under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.) and have been assigned OMB Control Number 2120-0056.
    (1) the operator's name;
    (2) the line number of the airplane;
    (3) a brief description of the damage detected; and
    (4) the amount of separation between the aileron control cable 
and the power feeder cable.
    (c) 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, Transport Airplane Directorate. 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.

    (d) 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.
    (e) The inspection, adjustment, and repair shall be done in 
accordance with Boeing Alert Service Bulletin 767-24A0113, Revision 
1, dated July 2, 1996. 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.
    (f) This amendment becomes effective on July 22, 1996, to all 
persons except those persons to whom it was made immediately 
effective by telegraphic AD T96-14-51, issued on July 3, 1996, which 
contained the requirements of this amendment.

    Issued in Renton, Washington, on July 10, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-17982 Filed 7-16-96; 8:45 am]
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