[Federal Register: October 29, 2008 (Volume 73, Number 210)]
[Proposed Rules]
[Page 64284-64286]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29oc08-25]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1117; Directorate Identifier 2008-NM-106-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Boeing Model 727 airplanes. This proposed AD would require inspections
for cracking of the left- and right-side shear ties and web posts of
the kickload beam and the adjacent structure in the vertical
stabilizer, and corrective actions if necessary. This proposed AD
results from a report of cracking of the left- and right-side web posts
and shear ties of the kickload beam. We are proposing this AD to detect
and correct cracking of the left- and right-side web posts and shear
ties of the kickload beam, which, when coupled with failures in the
adjacent structure, could result in structural failure of the vertical
stabilizer, and loss of control of the airplane.
DATES: We must receive comments on this proposed AD by December 15,
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,
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-2008-1117;
Directorate Identifier 2008-NM-106-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
[[Page 64285]]
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 a report of cracking of the left- and right-side
web posts and shear ties of the kickload beam. The cracking was
discovered during a scheduled maintenance visit of an airplane with
65,000 total flight hours and 42,000 total flight cycles. The reported
cracking of the left- and right-side web posts, which attach to the
kickload beam and the left- and right-side stringer 11 in the vertical
stabilizer, was due to stress corrosion caused by elevated fit up
stress. Cracking in the left- and right-side shear ties, which attach
to the kickload beam, was a result of fatigue caused by compensation
for cracking in the web posts. Cracking of the shear ties and web posts
can diminish the effectiveness of both left- and right-side stringer
11. When coupled with failures in the rear spar chord or stringer 10,
the critical crack length at which limit load can be sustained is
reduced, rendering the existing inspection intervals for stringer 10
and the rear spar chord insufficient. This condition, if not corrected,
could result in structural failure of the vertical stabilizer, which
could lead to loss of control of the airplane.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 727-55-
0093, dated March 12, 2008. The service bulletin describes procedures
for doing repetitive high frequency eddy current (HFEC) and low
frequency eddy current (LFEC) inspections for cracking of the left- and
right-side shear ties, left- and right-side web posts, left- and right-
side stringers 10 and 11, rear spar chord, associated critical
fasteners, and adjacent surfaces in the vertical stabilizer. For
airplanes on which any cracking is found in the shear ties or web
posts, the service bulletin describes replacing the cracked parts with
new parts and inspecting all open fastener holes in the kickload beam
web and chords for cracking. For airplanes on which cracking is found
in stringer 10 or 11, rear spar chord and skin, associated critical
fasteners, adjacent surfaces of the vertical stabilizer, or areas other
than the shear ties and web posts, the service bulletin specifies
contacting Boeing for repair instructions. The service bulletin
specifies the following compliance times:
Compliance Times
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Airplanes/condition Compliance time Repetitive interval
(whichever occurs first)
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Less than 52,000 total flight hours Before 56,000 total Before 42,000 total 10,000 flight hours or
or 39,000 total flight cycles. flight hours. flight cycles. 7,500 flight cycles,
whichever occurs
first.
More than 52,000 total flight hours Within 4,000 flight Within 3,000 flight 10,000 flight hours or
or 39,000 total flight cycles. hours after the date cycles after the date 7,500 flight cycles,
of the service of the service whichever occurs
bulletin. bulletin. first.
Any cracking found................... Before further flight.. ....................... (None).
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FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the(se) same type
design(s). This proposed AD would require accomplishing the actions
specified in the service information described previously, except as
discussed under ``Differences Between the Proposed AD and the Service
Bulletin.''
Differences Between the Proposed AD and the Service Bulletin
Boeing Special Attention Service Bulletin 727-55-0093, dated March
12, 2008, specifies to contact the manufacturer for instructions on how
to repair certain conditions, but this proposed AD would require
repairing those conditions in one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization, whom we have authorized to make those findings.
The service bulletin does not specify a compliance time for
airplanes with exactly 52,000 total flight hours or 39,000 total flight
cycles. We have grouped those airplanes with airplanes having ``less
than'' 52,000 total flight hours or 39,000 total flight cycles, as
specified in paragraph (g) of this proposed AD.
Interim Action
We consider this proposed AD interim action. If final action is
later identified, we might consider further rulemaking then.
Costs of Compliance
We estimate that this proposed AD would affect 364 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
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Average Number of
Work labor U.S.-
Action hours rate per Parts Cost per product registered Fleet cost
hour airplanes
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Inspection.................... 10 $80 $0 $800, per 364 $291,200, per
inspection cycle. inspection
cycle.
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[[Page 64286]]
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 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 this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979), and
3. 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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 FAA amends Sec. 39.13 by adding the following new AD:
Boeing: Docket No. FAA-2008-1117; Directorate Identifier 2008-NM-
106-AD.
Comments Due Date
(a) We must receive comments by December 15, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing 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 a report of cracking of the left- and
right-side web posts and shear ties of the kickload beam. We are
issuing this AD to detect and correct cracking of the left- and
right-side web posts and shear ties of the kickload beam, which,
when coupled with failures in the adjacent structure, could result
in structural failure of the vertical stabilizer, and loss of
control of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Inspections and Corrective Actions
(f) At the times specified in paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 727-55-0093, dated March
12, 2008 (``the service bulletin''), except as provided by
paragraphs (g) and (h) of this AD: Do the inspections to detect
cracking of the left- and right-side web posts and shear ties of the
kickload beam, by doing all of the actions specified in Part 2 and
the applicable corrective actions specified in Part 3 of the
Accomplishment Instructions of the service bulletin, except as
provided by paragraph (i) of this AD. Do all applicable corrective
actions before further flight. Repeat the inspections thereafter at
the intervals specified in paragraph 1.E. of the service bulletin.
Clarification and Exception to the Specified Compliance Times
(g) To determine the compliance times for airplanes having
exactly 52,000 total flight hours or 39,000 total flight cycles, for
the purposes of this AD, these airplanes are grouped with airplanes
having ``less than'' 52,000 total flight hours or 39,000 total
flight cycles, as specified in paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 727-55-0093, dated March
12, 2008.
(h) Where Boeing Special Attention Service Bulletin 727-55-0093,
dated March 12, 2008, 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.
Exception to the Specified Corrective Actions
(i) If any cracking is found during any inspection required by
this AD, and Boeing Special Attention Service Bulletin 727-55-0093,
dated March 12, 2008, specifies contacting Boeing for appropriate
action: Before further flight, repair the cracking or damage using a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA. For a repair method to be approved by the
Manager, Seattle ACO, as required by this paragraph, the Manager's
approval letter must specifically refer to this AD.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Seattle ACO, FAA, ATTN: Berhane Alazar,
Aerospace Engineer, Airframe Branch, ANM-120S, 1601 Lind Avenue,
SW., Renton, Washington 98057-3356; telephone (425) 917-6577; fax
(425) 917-6590; has the authority to approve AMOCs for this AD, if
requested using 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 October 10, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-25758 Filed 10-28-08; 8:45 am]
BILLING CODE 4910-13-P