[Federal Register: December 5, 2003 (Volume 68, Number 234)]
[Proposed Rules]
[Page 67973-67975]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05de03-17]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-198-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767-200, -300, and -300F
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Boeing Model 767-200, -
300, and -300F series airplanes. This proposal would require
performing, for both main landing gear (MLG), gap measurements of the
upper and lower joint gaps; an ultrasonic inspection of the outer
cylinder of the MLG for cracks between the downlock fitting attach
lugs; and follow-on and corrective actions if necessary. This action is
necessary to detect and correct cracks in the outer cylinder of the
MLG, which could result in collapsed MLG and consequent reduced
controllability of the airplane during takeoff and landing. This action
is intended to address the identified unsafe condition.
DATES: Comments must be received by January 20, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-198-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-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-198-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 or 2000 or
ASCII text.
The service information referenced in the proposed rule 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.
FOR FURTHER INFORMATION CONTACT: Suzanne Masterson, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6441; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications
[[Page 67974]]
received on or before the closing date for comments, specified above,
will be considered before taking action on the proposed rule. The
proposals contained in this action may be changed in light of the
comments received.
Submit comments using the following format:
[sbull] 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.
[sbull] For each issue, state what specific change to the proposed
AD is being requested.
[sbull] 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 proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2002-NM-198-AD.'' The postcard will be date stamped
and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 2002-NM-198-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received a report indicating that a crack was found on
the outer cylinder of the main landing gear (MLG) at the attach lugs
for the drag strut downlock fitting on a Model 767-300 series airplane.
The cause of the crack was due to heat damage from the upper bearing
rubbing on the cylinder. Excessive torque on the downlock fitting
attachment fasteners during production of Model 767-300 series
airplanes produced local deflection of the outer cylinder, causing
contact or interference with the upper bearing. This condition, if not
corrected, could result in cracks in the outer cylinder of the MLG,
which could result in collapsed MLG and consequent reduced
controllability of the airplane during takeoff and landing.
Similar Models
The subject area on certain Boeing Model 767-200 and -300F series
airplanes is almost identical to that on the affected Boeing Model 767-
300 series airplanes. Therefore, all of these models may be subject to
the same unsafe condition.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Service Bulletin 767-
32A0196, Revision 2, dated May 15, 2003, which describes procedures,
for both MLG, for performing gap measurements of the upper and lower
joint gaps (includes measuring and recording upper and lower joint gaps
twice); an ultrasonic inspection of the outer cylinder of the MLG for
cracks between the downlock fitting attach lugs; and follow-on and
corrective actions if necessary. The follow-on action includes
restoring the MLG (includes installing shims as applicable, electrical
bracket, and cotter pins; and marking the MLG). The corrective actions
include overhauling the outer cylinder of the MLG; replacing the outer
cylinder of the MLG with an interchangeable outer cylinder, and
contacting the manufacturer if there is any crack in the outer cylinder
that cannot be removed within the repair limits. Accomplishment of the
actions specified in the service bulletin is intended to adequately
address the identified unsafe condition.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require accomplishment of the actions specified in
the service bulletin described previously, except as discussed below.
Difference Between Proposed Rule and Service Bulletin
Operators should note that, although the service bulletin specifies
that the manufacturer may be contacted for disposition of certain
repair conditions, this proposal would require the repair to be
accomplished per a method approved by the FAA, or per data meeting the
type certification basis of the airplane approved by a Boeing Company
Designated Engineering Representative who has been authorized by the
FAA to make such findings.
Cost Impact
There are approximately 833 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 353 airplanes of U.S. registry
would be affected by this proposed AD, that it would take approximately
16 work hours per airplane to accomplish the proposed gap measurement
and inspection, and that the average labor rate is $65 per work hour.
Based on these figures, the cost impact of the proposed AD on U.S.
operators is estimated to be $367,120, or $1,040 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the proposed requirements
of this AD action, and that no operator would accomplish those actions
in the future if this proposed AD were not adopted. The cost impact
figures discussed in AD rulemaking actions represent only the time
necessary to perform the specific actions actually required by the AD.
These figures typically do not include incidental costs, such as the
time required to gain access and close up, planning time, or time
necessitated by other administrative actions. Manufacturer warranty
remedies may be available for labor costs associated with this proposed
AD. As a result, the costs attributable to the proposed AD may be less
than stated above.
Regulatory Impact
The regulations proposed herein 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. Therefore, it
is determined that this proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this 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) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
[[Page 67975]]
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Boeing: Docket 2002-NM-198-AD.
Applicability: Model 767-200, -300, and -300F series airplanes,
line numbers 1 through 883 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct cracks in the outer cylinder of the main
landing gear (MLG), which could result in collapsed MLG and
consequent reduced controllability of the airplane during takeoff
and landing, accomplish the following:
Service Bulletin References
(a) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Service Bulletin 767-32A0196,
Revision 2, dated May 15, 2003.
Inspection and Corrective Actions
(b) Within 18 months after the effective date of this AD, for
both MLG, do a gap measurement of the upper and lower joint gaps
(includes measuring and recording upper and lower joint gaps twice);
and an ultrasonic inspection of the outer cylinder of the main
landing gear for cracks between the downlock fitting attach lugs,
per Part 1 of the service bulletin.
(c) If no crack is found during the inspection required by
paragraph (b) of this AD, before further flight, do the restoration
(includes installing shims as applicable, electrical bracket, and
cotter pins; and marking the main landing gear) per the service
bulletin.
(d) If any crack is found during the inspection required by
paragraph (b) of this AD: Before further flight, overhaul the outer
cylinder of the MLG or replace the outer cylinder of the MLG with an
interchangeable outer cylinder per Part 2 of the service bulletin,
except as provided by paragraph (e) of this AD.
(e) If any crack is found in the outer cylinder that cannot be
removed within the repair limits specified in the service bulletin,
during the overhaul specified in paragraph (d) of this AD, and the
service bulletin specifies to contact Boeing for appropriate action:
Before further flight, repair per a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or per data
meeting the type certification basis of the airplane approved by a
Boeing Company Designated Engineering Representative who has been
authorized by the Manager, Seattle ACO, to make such findings. For a
repair method to be approved, the approval must specifically
reference this AD.
Note 1: When the outer cylinder is re-installed, attach the
downlock fittings onto the outer cylinder as specified in the
applicable Boeing Component Maintenance Manual (CMM), document
number 161T1000, Section 32-11-19, temporary revision (TR) 32-61,
dated March 26, 2002 or Section 32-11-19 pages 712 through 716 dated
July 01, 2002, or dated July 01, 2003; or CMM 32-11-20, TR 32-62,
dated March 26, 2002, or Section 32-11-20 pages 718 through 722
dated July 01, 2002, or dated July 01, 2003.
Actions Accomplished Per Previous Issue of Service Bulletin
(f) Accomplishment of the applicable actions before the
effective date of this AD per Boeing Service Bulletin 767-32A0196,
dated August 1, 2002; or, Revision 1, dated September 26, 2002; are
considered acceptable for compliance with the corresponding action
specified in this AD.
Parts Installation
(g) As of the effective date of this AD, no person may install a
MLG on any airplane, unless the outer cylinder of the MLG has been
inspected and follow-on and corrective actions have been
accomplished per Boeing Service Bulletin 767-32A0196, Revision 2,
dated May 15, 2003.
Alternative Methods of Compliance
(h) In accordance with 14 CFR 39.19, the Manager, Seattle
Aircraft Certification Office, FAA, is authorized to approve
alternative methods of compliance for this AD.
Issued in Renton, Washington, on November 28, 2003.
Kevin Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-30220 Filed 12-4-03; 8:45 am]
BILLING CODE 4910-13-P