[Federal Register Volume 63, Number 208 (Wednesday, October 28, 1998)]
[Rules and Regulations]
[Pages 57577-57578]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-28669]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 63, No. 208 / Wednesday, October 28, 1998 /
Rules and Regulations
[[Page 57577]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-281-AD; Amendment 39-10859; AD 98-22-12]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Boeing Model 767 series airplanes. This action
requires repetitive detailed visual inspections to detect cracked,
corroded, or stained collar fittings on both inboard trailing edge
flaps; and follow-on corrective actions, if necessary. This amendment
is prompted by a report indicating that a collar fitting suffered a
complete fracture as a result of stress corrosion cracking. The actions
specified in this AD are intended to prevent separation of the inboard
trailing edge flap from the airplane due to fractured collar fittings.
DATES: Effective November 12, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 12, 1998.
Comments for inclusion in the Rules Docket must be received on or
before December 28, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-281-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
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: Patrick Safarian, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (425) 227-2775; fax (425) 227-1181.
SUPPLEMENTARY INFORMATION: The FAA has received a report indicating
that an operator has found two collar fittings cracked or fractured on
an inboard trailing edge flap of a Boeing Model 767 series airplane.
The affected airplane was over 13 years old and had accumulated 28,300
total flight cycles at the time the failure was discovered. These
collar fittings are designed to attach the flap to the flap actuation
linkage. A fractured collar fitting could cause the inboard end of the
flap to become unrestrained, which in turn could lead to a separation
of the entire inboard trailing edge flap. Investigation has revealed
that the cracking initiated at corrosion pits on the internal splines
of the collar fitting; the cracking thereafter propagated due to stress
corrosion cracking until complete failure of the collar fitting
occurred.
Fractured collar fittings, if not detected and corrected, could
result in a separation of the inboard trailing edge flap and a
consequent reduction in the controllability of the airplane.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
767-57A0066, Revision 1, dated August 6, 1998, which describes
procedures for repetitive detailed visual inspections to detect
cracking, corrosion, or staining of the collar fittings on the inboard
trailing edge flap; and follow-on corrective actions, if necessary. The
follow-on corrective actions include replacing any collar fitting that
is found to be cracked and repairing any collar fitting that is found
to be corroded.
Explanation of the Requirement 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, this AD is
being issued to prevent separation of the inboard trailing edge flap
from the airplane due to fractured collar fittings. This AD requires
accomplishment of the actions specified in the Boeing alert service
bulletin described previously, except as discussed below.
Differences Between the Rule and the Relevant Service Information
Operators should note that, although the alert service bulletin
specifies that the manufacturer may be contacted for to obtain
instructions for certain repair conditions, this rule requires that the
repairs be accomplished in accordance with a method approved by the
FAA.
Operators should also note that although the alert service bulletin
specifies that certain repetitive detailed visual inspection intervals
are to be 30 days long, this rule allows these intervals to be extended
to 45 days. The longer interval provides an acceptable level of safety.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
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
[[Page 57578]]
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 98-NM-281-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:
98-22-12 Boeing: Amendment 39-10859. Docket 98-NM-281-AD.
Applicability: Model 767 series airplanes, line numbers 1
through 721 inclusive, 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 (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 prevent separation of the inboard trailing edge flap from the
airplane due to fractured collar fittings, accomplish the following:
(a) Within 8 years since the date of manufacture of the
airplane, or within 90 days after the effective date of this AD,
whichever occurs later, perform a detailed visual inspection of the
collar fittings of both inboard trailing edge flaps to detect
cracks, corrosion, or staining, in accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0066, Revision 1, dated August 6, 1998.
(1) If no cracked, corroded, or stained collar fitting is found,
repeat the detailed visual inspection required by paragraph (a) of
this AD thereafter at intervals not to exceed 120 days.
(2) If any cracked collar fitting is found, prior to further
flight, install a new collar fitting in accordance with Part 2 of
the Accomplishment Instructions of the alert service bulletin.
(3) If any corroded collar fitting is found, prior to further
flight, repair the corrosion in accordance with a method approved by
the Manager, Seattle Aircraft Certification Office (ACO), FAA,
Transport Airplane Directorate.
(4) If any stained collar fitting is found, accomplish the
requirements of paragraphs (a)(4)(i) and (a)(4)(ii) of this AD at
the compliance times specified.
(i) Repeat the detailed visual inspections required by paragraph
(a) of this AD thereafter at intervals not to exceed 45 days; and
(ii) Within 18 months after finding the stained collar fitting,
accomplish Part 2 of Accomplishment Instructions of the alert
service bulletin. If any corroded collar fitting is found, prior to
further flight, repair the corrosion in accordance with a method
approved by the Manager, Seattle ACO.
(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 ACO. 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.
(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.
(d) The inspections and installation shall be done in accordance
with Boeing Alert Service Bulletin 767-57A0066, Revision 1, dated
August 6, 1998. 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.
(e) This amendment becomes effective on November 12, 1998.
Issued in Renton, Washington, on October 21, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-28669 Filed 10-27-98; 8:45 am]
BILLING CODE 4910-13-U
