[Federal Register: June 14, 2005 (Volume 70, Number 113)]
[Rules and Regulations]
[Page 34313-34316]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14jn05-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21358; Directorate Identifier 2005-NM-088-AD;
Amendment 39-14120; AD 2005-12-04]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 757-200, -200PF, and -
200CB Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 757-200, -200PF, and -200CB series airplanes. This
AD requires repetitive inspections of the shim installation between the
vertical flange and bulkhead. This AD is prompted by reports of cracks,
loose and
[[Page 34314]]
broken bolts, and shim migration in the joint between the aft torque
bulkhead and the strut-to-diagonal brace fitting. We are issuing this
AD to detect and correct such cracks, loose and broken bolts, and shim
migration, which could result in damage to the strut and consequent
separation of the strut and engine from the airplane.
DATES: Effective June 29, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of June
29, 2005.
We must receive comments on this AD by August 15, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide Rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-21358; the directorate identifier for this docket is
2005-NM-088-AD.
Examining the Dockets
You can examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
(DMS) receives them.
FOR FURTHER INFORMATION CONTACT: Dennis Stremick, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6450; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: Boeing advises that, since 1993, it has
received 17 reports of cracks, loose and broken bolts, and shim
migration in the joint between the aft torque bulkhead and the strut-
to-diagonal brace fitting on Boeing Model 757-200 series airplanes.
Those conditions, if not corrected, could result in damage and
consequent loss of the strut and engine from the airplane.
Other Relevant Rulemaking
On May 25, 2004, we issued AD 2004-12-07, amendment 13666 (69 FR
33561, June 16, 2004). That AD applies to Boeing Model 757 series
airplanes, line numbers 1 through 735 inclusive, equipped with Rolls
Royce RB211 engines.
That AD requires modification of the nacelle strut and wing
structure; and inspections for loose/missing fasteners of certain aft
bulkhead fasteners, proper alignment of the middle gusset of the
inboard side load fitting, cracking of certain fastener holes; and
corrective action if necessary. That AD cites various revision levels
of Boeing Service Bulletin 757-54-0035 as the appropriate source of
service information for the required actions.
That AD also mandated inspections of the 20 fasteners that are
subject to this new AD. The threshold for those initial inspections is
15,000 total flight cycles. We have received reports of missing or
loose fasteners in the affected joint as low as approximately 7,500
total flight cycles. In addition, that AD mandated inspections of the
20 fasteners of airplanes modified in accordance with Boeing Service
Bulletin 757-54-0035 (original), but did not mandate inspections for
airplanes modified in accordance with Revisions 1 or 2 of that service
bulletin or airplanes that had been modified in production. Loose or
missing fasteners have been found on airplanes with all versions of the
modification.
The actions required by that AD were intended to prevent fatigue
cracking in primary strut structure and consequent reduced structural
integrity of the strut, but based on this service experience, we have
concluded that the inspection requirements of that AD are not adequate.
Relevant Service Information
We have reviewed Boeing Service Bulletin 757-54A0047, Revision 1,
dated March 24, 2005. The service bulletin describes procedures for
repetitive detailed inspections of the shim installation between the
vertical flange and bulkhead. Specifically, the service bulletin
provides procedures to:
Inspect for damaged sealant around the shim;
Inspect for signs of shim movement;
Measure the horizontal and vertical movement of the shim
from the installed position to determine the total cumulative movement
of the shims;
Inspect for signs of movement of the four fasteners in the
vertical flange; and
Detect signs of damaged paint and/or sealant or signs of
movement of the 16 fasteners that hold the bulkhead assembly to the
horizontal flange of the strut-to-diagonal brace fitting.
The service bulletin also describes four different interim repairs,
depending on the amount of shim movement revealed during the
inspections. The various interim repair actions include doing an eddy
current inspection of the fastener holes for cracks, for which the
service bulletin recommends contacting the manufacturer for repair
instructions; replacing the shims with new shims; oversizing the holes
and replacing discrepant fasteners with oversize fasteners; and
applying sealant/primer on the shim of the vertical flange.
For airplanes modified in accordance with Service Bulletin 757-54-
0035, the compliance time for the initial inspection is 6,000 flight
cycles/36 months after the modification, with a grace period of 3,000
flight cycles/18 months. For unmodified airplanes, the compliance time
is 90 days. The repetitive intervals range from 6,000 to 9,000 flight
cycles/36 to 54 months. Interim repairs are due before further flight
after a positive finding.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design. Therefore, we are
issuing this AD to detect and correct cracks, loose and broken bolts,
and shim migration in the joint between the aft torque bulkhead and the
strut-to-diagonal brace fitting. These conditions could result in
damage to the strut and consequent separation of the strut and engine
from the airplane. This AD requires accomplishing the actions specified
in the service information described previously, except as discussed
below.
[[Page 34315]]
Differences Between the AD and the Service Bulletin
The service bulletin specifies compliance times relative to the
issue date of the service bulletin; this AD requires corresponding
compliance times relative to the effective date of the AD.
The service bulletin specifies that you may contact the
manufacturer for instructions on how to repair certain conditions, but
this proposed AD would require you to repair those conditions using
either a method that we approve, or data that meet the certification
basis of the airplane and have been approved by an Authorized
Representative for the Boeing Delegation Option Authorization
Organization whom we have authorized to make those findings.
Clarification of Certain Compliance Times
For Group 2 airplanes, the service bulletin specifies an inspection
threshold relative to the date of issuance of the ``original
Airworthiness Certificate * * *'' For these same airplanes, however,
this AD requires an inspection threshold relative to the date of
issuance of the ``original standard airworthiness certificate * * *''
We find that the addition of the term ``standard'' will establish this
date with certainty.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed under ADDRESSES. Include ``Docket No. FAA-2005-21358;
Directorate Identifier 2005-NM-088-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of our docket
Web site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You can review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you can visit
http://dms.dot.gov.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that the 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. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
PART 39--AIRWORTHINESS DIRECTIVES
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-12-04 Boeing: Amendment 39-14120. Docket No. FAA-2005-21358;
Directorate Identifier 2005-NM-088-AD.
Effective Date
(a) This AD becomes effective June 29, 2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to Boeing Model 757-200, -
200PF, and -200CB series airplanes; certificated in any category;
line numbers 1 through 1048 inclusive; powered by Rolls Royce
engines.
Unsafe Condition
(d) This AD was prompted by reports of cracks, loose and broken
bolts, and shim migration in the joint between the aft torque
bulkhead and the strut-to-diagonal brace fitting. The FAA is issuing
this AD to detect and correct such conditions, which could result in
damage to the strut and consequent separation of the strut and
engine from the airplane.
Compliance: (e) You are responsible for having the actions
required by this AD performed within the compliance times specified,
unless the actions have already been done.
Service Information
(f) For purposes of this AD, ``the service bulletin'' refers to
Boeing Service Bulletin 757-54A0047, Revision 1, dated March 24,
2005.
Inspections
(g) Inspect the joint between the aft torque bulkhead and the
strut-to-diagonal brace fitting, and repair any loose shim or loose,
missing, or damaged fastener, by doing all actions at the times
specified in the Accomplishment Instructions of the service
bulletin, as applicable, except as required by paragraphs (i), (j),
and (k) of this AD.
(h) An inspection and corrective actions done before the
effective date of this AD in accordance with paragraph (b) or (c),
as applicable, of AD 2004-12-07, amendment 39-13666, are acceptable
for compliance
[[Page 34316]]
with the initial inspection requirement of paragraph (g) of this AD.
Exceptions to Service Bulletin Procedures
(i) Where the service bulletin specifies a compliance time
relative to the issue date of the service bulletin, this AD requires
compliance within the corresponding specified time relative to the
effective date of this AD.
(j) For purposes of this AD, for Group 2 airplanes having line
numbers 736 through 1048, the initial inspection must be done within
the specified time after the date of issuance of the original
standard airworthiness certificate or the date of issuance of the
original export certificate of airworthiness. The grace period for
these airplanes is 3,000 flights from the effective date of this AD.
(k) If any crack is found during any inspection required by this
AD, and the service bulletin specifies to contact Boeing for
appropriate action: Before further flight, repair the crack
according to a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or according to data meeting the
certification basis of the airplane approved by an Authorized
Representative for the Boeing Delegation Option Authorization
Organization who has been authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to be approved, the
approval must specifically refer to this AD.
Alternative Methods of Compliance (AMOCs)
(l) The Manager, Seattle ACO, has the authority to approve AMOCs
for this AD, if requested in accordance with the procedures found in
14 CFR 39.19.
(2) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Delegation Option
Authorization Organization who has been authorized by the Manager,
Seattle ACO, to make those findings. For a repair method to be
approved, the repair must meet the certification basis of the
airplane, and the approval must specifically refer to this AD.
Material Incorporated by Reference
(m) You must use Boeing Service Bulletin 757-54A0047, Revision
1, dated March 24, 2005, to perform the actions that are required by
this AD, unless the AD specifies otherwise. The Director of the
Federal Register approves the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To
get copies of the service information, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view
the AD docket, go to the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC. To review copies of the service
information, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at the
NARA, call (202) 741-6030, or go to http://www.archives.gov/
federal--register/code--of--federal--regulations/ ibr--
locations.html.
Issued in Renton, Washington, on May 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-11515 Filed 6-13-05; 8:45 am]
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