[Federal Register: November 26, 2007 (Volume 72, Number 226)]
[Proposed Rules]
[Page 65913-65916]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26no07-11]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0227; Directorate Identifier 2007-NM-159-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Boeing Model 727 airplanes. This proposed AD would require
repetitive inspections for cracking or corrosion of the threaded end of
the lower segment of the main landing gear (MLG) side strut, and
corrective actions if necessary. This proposed AD also would require
prior or concurrent inspection for cracking or corrosion of the threads
and thread relief area of the lower segment, corrective action if
necessary, and re-assembly using corrosion inhibiting compound. This
proposed AD results from reports of the threads cracking on the MLG
side strut lower segment. We are proposing this AD to prevent a
fractured side strut, which could result in collapse of the MLG.
DATES: We must receive comments on this proposed AD by January 10,
2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov.
Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, 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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
[[Page 65914]]
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6577; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0227;
Directorate Identifier 2007-NM-159-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received many reports of the threads cracking on the main
landing gear (MLG) side strut lower segment, on Boeing Model 727
airplanes. In one instance an operator reported hearing a loud noise
during taxiing after landing. The subsequent inspection revealed the
MLG side strut was broken at the threaded end of the lower segment,
causing the side strut to become detached from the shock strut. This
condition, if not corrected, could result in collapse of the MLG.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 727-32-
0338, Revision 4, dated April 7, 2007. The service bulletin describes
procedures for repetitive detailed and magnetic particle inspections
for cracking or corrosion of the threaded end of the lower segment of
the MLG side strut. The service bulletin also describes procedures for
corrective actions for corrosion or cracking. The corrective actions
include replacing the part with a serviceable part, repairing the part
as given in the Boeing Model 727 Overhaul Manual (OHM) 32-13-01, and
doing a modification of the lower segment. There are five
configurations for modification:
Option I Configuration--Blending out cracks and doing
thread root radiusing. This modification applies only to airplanes with
maximum taxi gross weight of 191,000 pounds and below.
Option II Configuration--Installing a new retainer nut,
locknut, lock washer, and seals. This modification applies only to
airplanes on which the segment is crack-free.
Option III Configuration--Removing 0.8-inch of the lower
end of the lower segment, inserting a spacer, and replacing the
retainer nut, locknut, lock washer, and seals.
Option IV Configuration--Similar to Option III, but also
removing additional lubrication on the retainer nut; and applying
corrosion inhibiting compound, rather than grease, to the threads at
re-assembly.
Option V Configuration--Replacing the side strut lower
segment with a larger-diameter spare (not production) part that has
fatigue improvement on the threads.
Boeing Special Attention Service Bulletin 727-32-0338, Revision 4,
also recommends the prior or concurrent accomplishment of the actions
specified in the table titled ``Prior/Concurrent Service Bulletins.''
The prior/concurrent service bulletins facilitate the overhaul and
repair procedures specified in Boeing Special Attention Service
Bulletin 727-32-0338, Revision 4.
Prior/Concurrent Service Bulletins
------------------------------------------------------------------------
Describes procedures
Boeing 727 service for these prior or
For-- bulletin-- concurrent actions--
------------------------------------------------------------------------
All airplanes............... 727-32-0411, Inspecting for
Revision 1, dated corrosion or
February 19, 2007. cracking of the
threads and thread
relief area of the
swivel clevis, and
improving the
corrosion
protection of the
swivel clevis
fitting threads in
commonly affected
airplanes.
Airplanes specified as 32-79, Revision 1, Modifying the MLG
Options III, IV and V dated February 27, side strut
configurations in Boeing 1967. universal joint.
Special Attention Service
Bulletin 727-32-0338,
Revision 4.
32-157, dated August Replacing the MLG
30, 1968. side strut swivel
bushing,
incorporating only
Parts Kit 65-89855-
1, and not
installing the lube
fitting in the
lower segment.
Airplanes specified as 727-32-268, Revision Inspecting and
Option V configuration in 2, dated February modifying the MLG
Boeing Special Attention 20, 1981. side strut.
Service Bulletin 727-32-
0338, Revision 4.
727-57-163, dated Resolving the
September 17, 1982. interference
between the MLG
gear beam and the
MLG side strut.
------------------------------------------------------------------------
Boeing Special Attention Service Bulletin 727-32-0338, Revision 4,
specifies that where any assembly, lubrication, or corrosion protection
procedure in a prior/concurrent service bulletin differs from those in
Boeing Special Attention Service Bulletin 727-32-0338, Revision 4,
operators should use the procedures in Boeing Special Attention Service
Bulletin 727-32-0338, Revision 4.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously.
Costs of Compliance
There are about 842 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 459 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with
[[Page 65915]]
this proposed AD. The average labor rate is $80 per work hour.
Estimated Costs
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Average labor
Action Work hours rate per hour Cost per airplane Fleet cost
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Inspection........................ 12 $80 $960, per inspection $440,640, per
cycle. inspection cycle.
Prior/concurrent actions.......... Up to 6 $80 Up to $480........... Up to $220,320.
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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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the 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. 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 proposed AD and placed it in the AD docket. 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2007-0227; Directorate Identifier 2007-NM-
159-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by January
10, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Model 727, 727C, 727-100, 727-100C,
727-200, and 727-200F series airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from reports of the threads cracking on the
main landing gear (MLG) side strut lower segment. We are issuing
this AD to prevent a fractured side strut, which could result in
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.
Inspections and Corrective Actions
(f) At the latest applicable time in paragraph (f)(1), (f)(2),
or (f)(3) of this AD: Do detailed and magnetic particle inspections
for cracking or corrosion of the threaded end of the lower segment
of the MLG side strut and do all applicable corrective actions as
specified in the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 727-32-0338, Revision 4, dated April 7,
2007. Do all applicable corrective actions before further flight.
Repeat the inspection thereafter at intervals not to exceed 120
months.
(1) Within 48 months after the last MLG overhaul.
(2) Within 6 months after the effective date of this AD.
(3) Within 120 months after the last MLG overhaul for airplanes
on which the actions in Boeing Special Attention Service Bulletin
727-32-0338, Revision 4, dated April 7, 2007, have been accomplished
before the effective date of this AD.
Prior/Concurrent Requirements
(g) Prior to or concurrently with the actions required by
paragraph (f) of this AD: Do all applicable actions specified in the
service bulletins listed in Table 1 of this AD. Where the
lubrication and corrosion protection procedures in any service
bulletin listed in Table 1 of this AD differ from those in Boeing
Special Attention Service Bulletin 727-32-0338, Revision 4, dated
April 7, 2007, use the procedures in Boeing Special Attention
Service Bulletin 727-32-0338, Revision 4.
Table 1.--Prior/Concurrent Requirements
------------------------------------------------------------------------
Describes procedures
For-- Boeing 727 service for these prior or
bulletin-- concurrent actions--
------------------------------------------------------------------------
(1) All airplanes........... 727-32-0411, Inspecting for
Revision 1, dated corrosion or
February 19, 2007. cracking of the
threads and thread
relief area of the
swivel clevis, and
improving the
corrosion
protection of the
swivel clevis
fitting threads in
commonly affected
airplanes.
[[Page 65916]]
(2) Airplanes specified as 32-79, Revision 1, Modifying the MLG
Options III, IV and V dated February 27, side strut
configurations in Boeing 1967. universal joint.
Special Attention Service
Bulletin 727-32-0338,
Revision 4.
32-157, dated August Replacing the MLG
30, 1968. side strut swivel
bushing,
incorporating only
Parts Kit 65-89855-
1, and not
installing the lube
fitting in the
lower segment.
(3) Airplanes specified as 727-32-268, Revision Inspecting and
Option V configuration in 2, dated February modifying the MLG
Boeing Special Attention 20, 1981. side strut.
Service Bulletin 727-32-
0338, Revision 4.
727-57-163, dated Resolving the
September 17, 1982. interference
between the MLG
gear beam and the
MLG side strut.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Seattle Aircraft Certification Office (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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) 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 Commercial Airplanes
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.
Issued in Renton, Washington, on November 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-22939 Filed 11-23-07; 8:45 am]
BILLING CODE 4910-13-P