[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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