Airworthiness Directives; Boeing Model 727 Airplanes, 65913-65916 [E7-22939]
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Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2007–0224;
Directorate Identifier 2007–NM–188–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 Boeing Model 737–
100, –200, –300, –400, and –500 series
airplanes, certificated in any category; as
identified in Boeing Service Bulletin 737–57–
1296, dated June 13, 2007.
Unsafe Condition
(d) This AD results from several reports of
cracks in the center wing box longitudinal
floor beams, upper chord, and lower chord.
We are issuing this AD to detect and correct
fatigue cracking of the upper and lower
chords and web of the longitudinal floor
beams, which could result in rapid loss of
cabin pressure.
ebenthall on PROD1PC69 with PROPOSALS
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.
Repetitive Inspections
(f) Do the various inspections for fatigue
cracks in the longitudinal floor beam web,
upper chord, and lower chord, located at the
applicable body stations specified in the
Accomplishment Instructions of Boeing
Service Bulletin 737–57–1296, dated June 13,
2007, by doing all the actions specified in the
Accomplishment Instructions of the service
bulletin, except as provided by paragraph (g)
of this AD. Do the inspections at the time
specified in paragraph (f)(1) or (f)(2) of this
AD, as applicable.
(1) For Groups 1 and 2 airplanes as
identified in the service bulletin: Do the
inspections at the applicable initial
compliance time listed in paragraph 1.E.,
‘‘Compliance,’’ of the service bulletin; except,
where the service bulletin specifies a
compliance time after the date on the service
bulletin, this AD requires compliance within
the specified compliance time after the
effective date of this AD. Repeat the
inspections thereafter at the intervals
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specified in paragraph 1.E., ‘‘Compliance,’’ of
the service bulletin.
(2) For Group 3 airplanes as identified in
the service bulletin: Do the inspections at the
applicable initial compliance time listed in
paragraph 1.E., ‘‘Compliance,’’ of the service
bulletin; except, where the service bulletin
specifies a compliance time after the date on
the service bulletin, this AD requires
compliance within the specified compliance
time after the effective date of this AD.
Repeat the inspections thereafter at the
intervals specified in paragraph 1.E.,
‘‘Compliance,’’ of the service bulletin.
(g) If any crack is found during any
inspection required by this AD, and Boeing
Service Bulletin 737–57–1296, dated June 13,
2007, specifies contacting Boeing for repair
instructions: Before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (h) of
this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(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) 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.
Issued in Renton, Washington, on
November 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–22928 Filed 11–23–07; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
PO 00000
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65913
Notice of proposed rulemaking
(NPRM).
ACTION:
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.
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
https://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.
DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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,
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Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
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 https://
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
For—
Boeing 727 service bulletin—
Describes procedures for these prior or concurrent actions—
All airplanes ........................................................
727–32–0411, Revision 1, dated February 19,
2007.
Airplanes specified as Options III, IV and V
configurations in Boeing Special Attention
Service Bulletin 727–32–0338, Revision 4.
32–79, Revision 1, dated February 27, 1967 ..
Inspecting for corrosion or 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.
Modifying the MLG side strut universal joint.
32–157, dated August 30, 1968 ......................
Airplanes specified as Option V configuration in
Boeing Special Attention Service Bulletin
727–32–0338, Revision 4.
727–32–268, Revision 2, dated February 20,
1981.
ebenthall on PROD1PC69 with PROPOSALS
727–57–163, dated September 17, 1982 ........
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.
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Replacing the MLG side strut swivel bushing,
incorporating only Parts Kit 65–89855–1,
and not installing the lube fitting in the
lower segment.
Inspecting and modifying the MLG side strut.
Resolving the interference between the MLG
gear beam and the MLG side strut.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
proposing this AD, which would require
accomplishing the actions specified in
the service information described
previously.
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
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
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Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
this proposed AD. The average labor
rate is $80 per work hour.
ESTIMATED COSTS
Action
Work hours
Average labor
rate per hour
Cost per airplane
Inspection ....................................................................
12
$80
$960, per inspection cycle
Prior/concurrent actions ..............................................
Up to 6
$80
Up to $480 .......................
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.
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.
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
§ 39.13
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.
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 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
Fleet cost
$440,640, per inspection
cycle.
Up to $220,320.
(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.
ebenthall on PROD1PC69 with PROPOSALS
TABLE 1.—PRIOR/CONCURRENT REQUIREMENTS
For—
Boeing 727 service bulletin—
Describes procedures for these prior or concurrent actions—
(1) All airplanes ..................................................
727–32–0411, Revision 1, dated February 19,
2007.
Inspecting for corrosion or 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.
VerDate Aug<31>2005
15:37 Nov 23, 2007
Jkt 214001
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Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
TABLE 1.—PRIOR/CONCURRENT REQUIREMENTS—Continued
Describes procedures for these prior or concurrent actions—
For—
Boeing 727 service bulletin—
(2) Airplanes specified as Options III, IV and V
configurations in Boeing Special Attention
Service Bulletin 727–32–0338, Revision 4.
32–79, Revision 1, dated February 27, 1967 ..
Modifying the MLG side strut universal joint.
32–157, dated August 30, 1968 ......................
Replacing the MLG side strut swivel bushing,
incorporating only Parts Kit 65–89855–1,
and not installing the lube fitting in the
lower segment.
Inspecting and modifying the MLG side strut.
(3) Airplanes specified as Option V configuration in Boeing Special Attention Service Bulletin 727–32–0338, Revision 4.
727–32–268, Revision 2, dated February 20,
1981.
727–57–163, dated September 17, 1982 ........
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
DEPARTMENT OF ENERGY
Federal Energy Regulatory
Commission
18 CFR Part 284
ebenthall on PROD1PC69 with PROPOSALS
[Docket No. RM08–1–000]
Promotion of a More Efficient Capacity
Release Market
November 15, 2007.
Federal Energy Regulatory
Commission, Department of Energy.
ACTION: Notice of Proposed Rulemaking.
AGENCY:
VerDate Aug<31>2005
17:18 Nov 23, 2007
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SUMMARY: The Federal Energy
Regulatory Commission is proposing
revisions to its regulations governing
interstate natural gas pipelines to reflect
changes in the market for short-term
transportation services on pipelines and
to improve the efficiency of the
Commission’s capacity release
mechanism. The Commission is
proposing to permit market based
pricing for short-term capacity releases
and to facilitate asset management
arrangements by relaxing the
Commission’s prohibition on tying and
on its bidding requirements for certain
capacity releases.
DATES: Comments are due January 10,
2008.
You may submit comments,
identified by docket number by any of
the following methods:
Agency Web site: https://ferc.gov.
Documents created electronically using
word processing software should be
filed in native applications or print-toPDF format and not in a scanned format.
Mail/Hand Delivery: Commenters
unable to file comments electronically
must mail or hand deliver an original
and 14 copies of their comments to:
Federal Energy Regulatory Commission,
Secretary of the Commission, 888 First
Street, NE., Washington, DC 20426.
Instructions: For detailed instructions
on submitting comments and additional
information on the rulemaking process,
see the Comment Procedures section of
this document.
FOR FURTHER INFORMATION CONTACT:
Robert McLean, Office of the General
Counsel, Federal Energy Regulatory
Commission, 888 First Street, NE.,
Washington, DC 20426,
Robert.McLean@ferc.gov, (202) 502–
8156.
David Maranville, Office of the General
Counsel, Federal Energy Regulatory
Commission, 888 First Street, NE.,
Washington, DC 20426,
ADDRESSES:
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Resolving the interference between the MLG
gear beam and the MLG side strut.
David.Maranville@ferc.gov, (202) 502–
6351.
SUPPLEMENTARY INFORMATION:
Notice of Proposed Rulemaking
Table of Contents
Paragraph
numbers
I. Background ...........................
A. The Capacity Release
Program .............................
B. Petitions and Industry
Comments .........................
II. Removal of Maximum Rate
Ceiling for Short-Term Capacity Release ......................
A. Policies Enhancing Competition ...............................
B. Data on Capacity Release
Transactions ......................
C. Available Pipeline Service
Constrains Market Power
Abuses ...............................
D. Monitoring .........................
E. Requests to Expand Market-Based Rate Authority ..
1. Removal of Price Ceiling
for Long-Term Releases
2. Removal of Price Ceiling
for Pipeline Short-Term
Transactions ..................
III. Asset Management Arrangements ....................................
A. Background ......................
B. Discussion ........................
1. Tying ..............................
2. The Bidding Requirement ...............................
3. Definition of AMAs .........
IV. State Mandated Retail
Choice Programs ..................
V. Shipper Must-Have-Title Requirement ..............................
VI. Regulatory Requirements ...
A. Information Collection
Statement ..........................
B. Environmental Analysis ....
C. Regulatory Flexibility Act ..
D. Comment Procedures ......
E. Document Availability .......
2.
2.
15.
23.
30.
33.
40.
42.
43.
43.
46.
53.
53.
63.
75.
83.
91.
97.
106.
111.
111.
114.
115.
117.
121.
1. In this Notice of Proposed
Rulemaking, the Commission proposes
to revise its Part 284 regulations
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]]>Agencies
[Federal Register Volume 72, Number 226 (Monday, November 26, 2007)]
[Proposed Rules]
[Pages 65913-65916]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22939]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 https://
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 https://
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 https://
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
----------------------------------------------------------------------------------------------------------------
Average labor
Action Work hours rate per hour Cost per airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
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
