[Federal Register: March 11, 2005 (Volume 70, Number 47)]
[Rules and Regulations]
[Page 12120-12124]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11mr05-8]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19530; Directorate Identifier 2002-NM-274-AD;
Amendment 39-14008; AD 2005-05-19]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 727 airplanes. That AD
currently requires repetitive detailed inspections to detect cracking,
corrosion, and existing stop-drilled repairs of cracking in the upper
chord of the rear spar of the wing; and repair if necessary. This new
AD requires new repetitive inspections to detect cracks, corrosion,
minor surface defects, and existing stop-drilled repairs of cracks in
the upper and lower chords of the front and rear spars of the wing; and
repair if necessary. This AD is prompted by our determination that
further rulemaking action is necessary to require additional actions
specified in the referenced service bulletin. We are issuing this AD to
prevent structural failure of the wing and fuel leaks in the airplane
due to stress corrosion cracking of the wing spar chords.
DATES: This AD becomes effective April 15, 2005.
On December 18, 2002 (67 FR 71808, December 3, 2002), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 727-57A0145, Revision 2, dated October
24, 2002.
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-2004-19530; the directorate
identifier for this docket is 2002-NM-274-AD.
FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6456; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR Part 39) with an AD to supersede
AD 2002-24-05, amendment 39-12970 (67 FR 71808, December 3, 2002). The
existing AD applies to certain Boeing Model 727 airplanes. The proposed
AD was published in the Federal Register on November 5, 2004 (69 FR
64506), to require new repetitive inspections to detect cracks,
corrosion, minor surface defects, and existing stop-drilled repairs of
cracks in the upper and lower chords of the front and rear spars of the
wing; and repair if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that has been
submitted on the proposed AD. The commenter supports the proposed AD.
Explanation of Change to Model Designation
We have revised the subject heading of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
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
comment that has been submitted, and determined that air safety and the
public interest require adopting the AD with the change described
previously. We have determined that this change will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 1,426 airplanes of the affected design in the
worldwide fleet. This AD will affect about 946 airplanes of U.S.
registry.
For Group 1 airplanes identified in the service bulletin, the
actions (Part 1 of the Accomplishment Instructions of the service
bulletin) that are required by AD 2002-24-05 and retained in this AD
take about 8 work hours per airplane, at an average labor rate of $65
per work hour. Based on these figures, the estimated cost of the
currently required actions is $520 per airplane.
The following table provides the estimated costs for U.S. operators
to comply with the new actions required by this AD. The average labor
rate is $65 per work hour.
[[Page 12121]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Per airplane
cost, per
For airplanes identified in the service bulletin as-- Actions in-- Work hours-- inspection
cycle--
--------------------------------------------------------------------------------------------------------------------------------------------------------
Group 1.............................................................................. Part 2 of the Accomplishment 30 $1,950
Instructions of the service
bulletin.
Group 1.............................................................................. Part 3 of the Accomplishment 21 1,365
Instructions of the service
bulletin.
Group 1.............................................................................. Part 4 of the Accomplishment 68 4,420
Instructions of the service
bulletin.
Group 1.............................................................................. Part 8 of the Accomplishment 8 520
Instructions of the service
bulletin.
Group 1.............................................................................. Part 9 of the Accomplishment 30 1,950
Instructions of the service
bulletin.
Group 2.............................................................................. Part 5 of the Accomplishment 52 3,380
Instructions of the service
bulletin.
Group 2.............................................................................. Part 6 of the Accomplishment 110 7,150
Instructions of the service
bulletin.
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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 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 removing amendment 39-12970 (67 FR
71808, December 3, 2002), and by adding the following new airworthiness
directive (AD):
2005-05-19 Boeing: Amendment 39-14008. Docket No. FAA-2004-19530;
Directorate Identifier 2002-NM-274-AD.
Effective Date
(a) This AD becomes effective April 15, 2005.
Affected ADs
(b) This AD supersedes AD 2002-24-05, amendment 39-12970.
Applicability
(c) This AD applies to Boeing Model 727, 727C, 727-100, -100C, -
200, and -200F series airplanes, line numbers 1 through 1832
inclusive; certificated in any category.
Unsafe Condition
(d) This AD was prompted by our determination that further
rulemaking action is necessary to require additional actions
specified in the referenced service bulletin. We are issuing this AD
to prevent structural failure of the wing and fuel leaks in the
airplane due to stress corrosion cracking of the wing spar chords.
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 Bulletin References
(f) The term ``the service bulletin,'' as used in this AD, means
Boeing Alert Service Bulletin 727-57A0145, Revision 2, dated October
24, 2002.
Inspection Requirements of AD 2002-24-05, Amendment 39-12970
Inspection
(g) For airplanes specified as ``Group 1'' airplanes in the
service bulletin: Within 20 years after the date of manufacture or
within 90 days after December 18, 2002 (the effective date of AD
2002-24-05, amendment 39-12970), whichever occurs later, perform an
external detailed inspection for cracking, corrosion, and existing
stop-drilled repairs of cracking in the upper chord on the rear spar
from Wing Butt Line (WBL) 70.5 through WBL 249.3, per the service
bulletin, paragraph 3.B, ``Work Instructions,'' Part 1. Thereafter,
repeat the inspection at intervals not to exceed 2 years.
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.''
[[Page 12122]]
New Actions Required by This AD
Inspections Specified in Parts 2 Through 6, and 8 and 9 of the
Service Bulletin
(h) Accomplish the applicable inspection(s) specified in
paragraphs (h)(1) through (h)(7) of this AD at the later of the
applicable times specified in the ``Threshold'' and ``Grace Period''
columns in Table 1 of this AD, and repeat the inspection(s) at the
time specified in the ``Repetitive Interval'' column of Table 1 of
this AD. Accomplishment of the inspection required by paragraph
(h)(1) of this AD terminates the repetitive inspection requirements
of paragraph (g) of this AD.
Table 1.--Compliance Times for Inspections Specified in Parts 2 Through 6, and 8 and 9 of Service Bulletin
----------------------------------------------------------------------------------------------------------------
For airplanes identified in the Repetitive
service bulletin as-- Threshold-- Grace period-- interval-- Do--
----------------------------------------------------------------------------------------------------------------
(1) Group 1..................... Before 20 years Within 1 year None.............. A high frequency
since the date of after the eddy current
issuance of the effective date of (HFEC) inspection
original this AD. and detailed
Airworthiness inspection of the
Certificate or upper chord the
the date of rear spar from
issuance of the WBL 70.5 to the
original Export wing tip for
Certificate of cracks,
Airworthiness. corrosion, minor
surface defects,
and existing stop-
drilled repairs
of cracking, in
accordance with
paragraph 3.B.,
Work
Instructions,
Part 2, of the
Accomplishment
Instructions of
the service
bulletin.
(2) Group 1..................... Before 20 years Within 2 years At intervals not A detailed
since the date of after the to exceed 2 years. inspection of the
issuance of the effective date of upper and lower
original this AD. chord of the
Airworthiness front spar and
Certificate or the lower chord
the date of of the rear spar
issuance of the from WBL 70.5 to
Original Export the wing tip for
Certificate of cracks,
Airworthiness. corrosion, minor
surface defects,
and existing stop-
drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 3, of the
Accomplishment
Instructions of
the service
bulletin.
(3) Group 1..................... Before 20 years Within 4 years At intervals not An HFEC inspection
since the date of after the to exceed 4 years. of the upper and
issuance of the effective date of lower chords of
original this AD. the rear spar
Airworthiness from WBL 70.5 to
Certificate or the wing tip for
the date of cracks,
issuance of the corrosion, minor
original Export surface defects,
Certificate of and existing stop-
Airworthiness. drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 4, of the
Accomplishment
Instructions of
the service
bulletin.
(4) Group 1..................... Within 2 years None.............. At intervals not A detailed
after doing the to exceed 2 years. inspection of the
actions required upper chord of
by paragraph the rear spar WBL
(h)(1) of this AD. 70.5 to the wing
tip for cracks,
corrosion, minor
surface defects,
and existing stop-
drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 8, of the
Accomplishment
Instructions of
the service
bulletin.
[[Page 12123]]
(5) Group 1..................... Within 4 years None.............. At intervals not An HFEC inspection
after doing the to exceed 4 years. of doing the not
actions required to the upper
by paragraph chord actions
(h)(1) of this AD. exceed 4 of the
rear spar
required by years
from WBL 70.5 to
paragraph the
wing tip for
(h)(1) of cracks,
this AD
corrosion, minor
surface defects,
and existing stop-
drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 9, of the
Accomplishment
Instructions of
the service
bulletin.
(6) Group 2..................... Before 20 years Within 2 years At intervals not An exterior
since the date of after the to exceed 2 years. detailed
issuance of the effective date of inspection of the
original this AD. upper and lower
Airworthiness chords of the
Certificate or front and rear
the date of spars from WBL
issuance of the 70.5 to the wing
original Export tip for cracks,
Certificate of corrosion, minor
Airworthiness. surface defects,
and existing stop-
drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 5, of the
Accomplishment
Instructions of
the service
bulletin.
(7) Group 2..................... Before 20 years Within 4 years At intervals not An HFEC inspection
since the date of after the to exceed 4 years. of the upper and
issuance of the effective date of lower chords of
original this AD. the front and
Airworthiness rear spars from
Certificate or WBL 70.5 to the
the date of wing tip for
issuance of the cracks,
original Export corrosion, minor
Certificate of surface defects,
Airworthiness. and existing stop-
drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 6, of the
Accomplishment
Instructions of
the service
bulletin.
----------------------------------------------------------------------------------------------------------------
Corrective Actions
(i) If any crack, corrosion, or minor surface defect is detected
during any inspection required by this AD, before further flight, do
the applicable corrective actions in accordance with Part 7 of the
Accomplishment Instructions of the service bulletin, except as
provided by paragraph (j) of this AD.
(j) If any crack or corrosion is detected during any inspection
required by this AD that exceeds the limits specified in the service
bulletin, and the 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 in accordance with 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 such findings. For a repair method to be approved, the approval
must specifically reference this AD.
(k) If any existing stop-drilled repair of previous cracking is
detected during any inspection required by this AD, before further
flight, permanently repair crack in accordance with paragraph 3.B.,
Work Instructions, Part 7, paragraph 2., ``Crack Repair'' of the
Accomplishment Instructions of the service bulletin.
(l) Before further flight following any inspection or repair
required by this AD, apply a wet layer of BMS 3-23 organic corrosion
inhibiting compound or Boeing equivalent, in accordance with the
Accomplishment Instructions of the service bulletin.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19.
(2) Alternative methods of compliance, approved previously in
accordance with AD 2002-24-05, amendment 39-12970, are
[[Page 12124]]
approved as alternative methods of compliance with this AD.
(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 Delegation Option
Authorization 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.
Material Incorporated by Reference
(n) You must use Boeing Alert Service Bulletin 727-57A0145,
Revision 2, dated October 24, 2002, to perform the actions that are
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register previously approved the incorporation by
reference of this document as of December 18, 2002 (67 FR 71808,
December 3, 2002). For copies of the service information, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207. For information on the availability of this material at
the National Archives and Records Administration (NARA), call (202)
741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
You may view the AD
docket at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW, room PL-401, Nassif Building,
Washington, DC.
Issued in Renton, Washington, on March 2, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-4826 Filed 3-10-05; 8:45 am]
BILLING CODE 4910-13-P