[Federal Register: September 6, 2005 (Volume 70, Number 171)]
[Rules and Regulations]
[Page 52899-52902]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06se05-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18877; Directorate Identifier 2002-NM-340-AD;
Amendment 39-14248; AD 2005-18-08]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, -200C, and
-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 737-100, -200, -200C, and -300 series airplanes.
This AD requires repetitive detailed inspections to detect
discrepancies of the retaining pin lugs on the support fitting of the
main landing gear (MLG) beam, and rework of the support fitting, or
replacement of the fitting if necessary. This AD is prompted by reports
of discrepancies of the lugs. We are issuing this AD to prevent
separation of the support beam of the MLG from the rear spar, which
could cause cracking of the MLG support fitting and a consequent leak
in the wing fuel tank or collapse of the MLG.
DATES: This AD becomes effective October 11, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of
October 11, 2005.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. 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 U.S.
Department of Transportation, 400 Seventh Street, SW., room PL-401,
Washington, DC. This docket number is FAA-2004-18877; the directorate
identifier for this docket is 2002-NM-340-AD.
FOR FURTHER INFORMATION CONTACT: Robert C. Hardwick, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6457; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with an AD for certain Boeing Model 737-100, -200, -200C, and -300
series airplanes. That action, published in the Federal Register on
August 17, 2004 (69 FR 51017), proposed to require repetitive detailed
inspections to detect discrepancies of the retaining pin lugs on the
support fitting of the main landing gear (MLG) beam, and rework of the
support fitting or replacement of the fitting if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD.
Agreement With the Proposed AD
One commenter, the manufacturer, agrees with the proposed AD.
Conditional Agreement With the Proposed AD
One commenter, an operator, agrees with the proposed AD provided
that there are adequate parts available if the discrepant condition is
found.
The FAA agrees that adequate availability of parts is necessary. We
[[Page 52900]]
have received no information from the manufacturer concerning a
possible delay in availability of parts. In the event there is a delay
in the availability of parts, an operator may request approval for an
alternative method of compliance as specified in paragraph (k)(1) of
this AD.
Request for Clarification of Paragraph (g) of the Proposed AD
One commenter, an operator, requests additional information and
clarification regarding the reference in paragraph (g)(2) of the
proposed AD to replacing the fittings in accordance with the
Accomplishment Instructions, Part III--Fitting Replacement, of Boeing
Service Bulletin 737-57-1216, Revision 2, dated May 6, 1999. The
commenter notes that, in certain situations, those Accomplishment
Instructions instruct the operator to install a self-locking nut to
secure the support pin of the MLG support beam. However, the commenter
advises that installing a self-locking nut would be in conflict with AD
2002-02-08 (67 FR 6372, February 12, 2002).
We agree that clarification of paragraph (g)(2) of the AD is
necessary in order to prevent a conflict between the requirements of
this AD and AD 2002-02-08. Therefore, we have added further information
to paragraph (g)(2) of the AD to specify that, if operators choose to
accomplish the corrective action specified in paragraph (g)(2) of the
AD, replacing the fitting in accordance with the Accomplishment
Instructions, Part III--Fitting Replacement, of Boeing Service Bulletin
737-57-1216, Revision 2, dated May 6, 1999, must also include replacing
the retaining bolt, self-locking nut, and associated hardware of the
support beam for the MLG with a new bolt, castellated nut, and new
hardware; in accordance with Boeing Service Bulletin 737-57A1260,
Revision 2, dated October 18, 2001.
Request for Credit for Accomplishing Certain Service Bulletins
One commenter, an operator, requests that the original issue, dated
December 17, 1992, and Revision 1, dated September 23, 1993, of Boeing
Service Bulletin 737-57-1216 be approved as acceptable for terminating
the requirements of the proposed AD. The commenter states that the
original issue and Revision 1 provide procedures for replacing the
fitting that are essentially the same as those in Revision 2, which is
cited as the appropriate service information in paragraph (g)(2) of the
proposed AD.
We agree with the commenter for the reason stated and have revised
paragraph (g)(2) of the AD accordingly.
Request To Clarify Paragraph (j) of the Proposed AD
One commenter, an operator, requests that the fittings acceptable
for installation be stated in a more definite manner than ``a new
lug.'' The commenter suggests that paragraph (j) of the proposed AD be
revised to specify a part number or serial number, rather than just ``a
new lug.'' The commenter also requests that the inspection and rework
instructions of paragraph (j) of the proposed AD be more specific.
We agree that clarifying the intent of the words ``new lug'' is
necessary. Although the inspection requirements of this AD are intended
to detect cracking of ``the retaining pin lugs of the support fitting
of the MLG, or elongation of a bolt hole in a lug,'' the corrective
actions of paragraph (g) of this AD require reworking or replacing the
fittings. We specify reworking or replacing the fittings, rather than
the lugs, since the lugs are not available as individual replacement
parts. The intent and purpose of paragraph (j) of this AD is to specify
that any lug must be inspected and the fitting reworked or replaced, as
applicable, except for those fittings that previously have been
reworked or replaced, in accordance with paragraph (g) of this AD. We
have revised paragraph (j) of the AD accordingly. We do not, however,
agree that the inspection and rework instructions of paragraph (j) of
the AD need to be more specific. The requirements of paragraph (j) of
the AD indicate multiple actions that are clearly encompassed by
stating ``in accordance with this AD,'' rather than to specify each
action that has already been stated in previous paragraphs of the AD.
Changes to Delegation Authority
Boeing has received a Delegation Option Authorization (DOA). We
have revised this final rule to delegate the authority to approve an
alternative method of compliance for any repair required by this AD to
the Authorized Representative for the Boeing DOA Organization rather
than the Designated Engineering Representative (DER).
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 1,670 airplanes worldwide of the affected design
and 668 airplanes of U.S. registry. The required actions take about 2
work hours per airplane, at an average labor rate of $65 per work hour.
Based on these figures, the estimated cost of the required actions for
U.S. operators is $86,840, or $130 per airplane, per inspection cycle.
The rework, if accomplished, will take about 24 work hours per
airplane to accomplish at an average labor rate of $65 per work hour.
Required parts will cost about $1,006 per airplane. Based on these
figures, the cost impact of the rework provided by this AD is estimated
to be $2,566 per airplane.
The replacement of the support fitting of the MLG beam, if
accomplished, will take about 128 work hours per airplane to accomplish
at an average labor rate of $65 per work hour. Required parts will cost
between $4,540 and $5,271 per airplane. Based on these figures, the
cost impact of the replacement provided by this AD is estimated to be
between $12,860 and $13,591 per airplane.
The replacement of the support fitting and installation of a
special bushing of the MLG beam (for Group 9 and Group 10 airplanes),
if accomplished, will take about 144 work hours per airplane to
accomplish at an average labor rate of $65 per work hour. Required
parts will cost about $5,081 per airplane. Based on these figures, the
cost impact of this replacement and installation is estimated to be
$14,441 per airplane.
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.
[[Page 52901]]
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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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):
2005-18-08 Boeing: Amendment 39-14248. Docket No. FAA-2004-18877;
Directorate Identifier 2002-NM-340-AD.
Effective Date
(a) This AD becomes effective October 11, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-100, -200, -200C, and -
300 series airplanes, certificated in any category; line numbers 1
through 1670 inclusive.
Unsafe Condition
(d) This AD was prompted by reports of discrepancies of the lugs
on the support fitting of the main landing gear (MLG) beam. We are
issuing this AD to prevent separation of the support beam of the MLG
from the rear spar, which could cause cracking of the MLG support
fitting and a consequent leak in the wing fuel tank or collapse of
the MLG.
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.
Inspection
(f) Prior to the accumulation of 15,000 total flight cycles, or
within 3,000 flight cycles after the effective date of this AD,
whichever occurs later: Perform a detailed inspection to detect
cracking of the retaining pin lugs of the support fitting of the MLG
beam, or elongation of a bolt hole in a lug, in accordance with the
Accomplishment Instructions, Part I: Inspection, of Boeing Special
Attention Service Bulletin 737-57-1267, dated August 8, 2002. If no
cracked lug or elongated bolt hole is found, repeat the inspection
thereafter at intervals not to exceed 12,000 flight cycles, until
the actions specified in paragraph (h) of this AD are accomplished.
Note 1: For the purposes of this AD, a detailed inspection is
``an intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirrors magnifying lenses, etc. may be necessary. Surface cleaning
and elaborate procedures may be required.''
Corrective Action
(g) If any cracked lug or elongated bolt hole is found during
any inspection required by paragraph (f) of this AD, before further
flight, do paragraph (g)(1) or (g)(2) of this AD.
(1) Rework the fitting in accordance with the Accomplishment
Instructions, Part II: Rework, of Boeing Special Attention Service
Bulletin 737-57-1267, dated August 8, 2002.
(2) Replace the fitting in accordance with the Accomplishment
Instructions, Part III--Fitting Replacement, of Boeing Service
Bulletin 737-57-1216, Revision 2, dated May 6, 1999, and install a
retaining bolt, castellated nut, and cotter pin in accordance with
Boeing Service Bulletin 737-57A1260, Revision 2, dated October 18,
2001. Replacing the fitting in accordance with the Accomplishment
Instructions, Part III--Fitting Replacement, of Boeing Service
Bulletin 737-57-1216, dated December 17, 1992, or Revision 1, dated
September 23, 1993; and replacing the retaining bolt, self-locking
nut, and associated hardware of the support beam for the MLG with a
new bolt, castellated nut, and new hardware; in accordance with
Boeing Service Bulletin 737-57A1260, Revision 2, dated October 18,
2001; prior to the effective date of this AD are acceptable methods
of compliance with the requirements of this paragraph.
Optional Terminating Action
(h) Reworking or replacing the fitting in accordance with
paragraph (g)(1) or (g)(2) of this AD constitutes terminating action
for the inspections required by paragraph (f) of this AD.
Repair
(i) If any cracking is found during any inspection required by
this AD, and the service bulletin specifies to contact Boeing for
appropriate action: Before further flight, repair in accordance with
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 an Authorized Representative (AR) for
the Boeing DOA Organization 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.
Parts Installation
(j) As of the effective date of this AD: With the exception of a
new support fitting of the MLG; (i.e., a fitting that has been
reworked or replaced as required by paragraph (g) of this AD), all
retaining pin lugs of the support fitting, and bolt holes of the
lugs must be inspected in accordance with this AD before being
installed on any airplane.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle ACO, FAA, 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 corrective actions per data meeting the type certification
basis of the airplane approved by a Boeing DOA Organization AR 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 reference this AD.
Material Incorporated by Reference
(l) You must use Boeing Special Attention Service Bulletin 737-
57-1267, dated August 8, 2002; Boeing Service Bulletin 737-57-1216,
Revision 2, dated May 6, 1999; and Boeing Service Bulletin 737-
57A1260, Revision 2, dated October 18, 2001; as applicable, 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 these documents 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 an 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
.
[[Page 52902]]
Issued in Renton, Washington, on August 24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-17461 Filed 9-2-05; 8:45 am]
BILLING CODE 4910-13-P