[Federal Register: April 7, 2006 (Volume 71, Number 67)]
[Rules and Regulations]
[Page 17696-17698]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07ap06-3]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23672; Directorate Identifier 2005-NM-237-AD;
Amendment 39-14544; AD 2006-07-17]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727-
100C, and 727-200 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing transport category airplanes. This AD requires
determining if the terminal fittings of the spars of the wings are made
of 7079 aluminum alloy material. For any positive finding, the AD
requires doing repetitive inspections for cracks and corrosion of all
exposed surfaces of the terminal fitting bores; doing repetitive
inspections for cracks, corrosion, and other surface defects, of all
exposed surfaces, including the flanges, of the terminal fitting;
applying corrosion inhibiting compound to the terminal fittings; and
repairing or replacing any cracked, corroded, or defective part with a
new part. This AD also provides for an optional terminating action for
the repetitive inspections. This AD results from reports of cracking of
the terminal fittings of the spars of the wings. We are issuing this AD
to detect and correct stress-corrosion cracking of the terminal
fittings, which could result in the failure of one of the terminal
fitting connections. Such a failure, combined with a similar failure of
one of the other three terminal fittings, could result in the inability
of the airplane structure to carry fail-safe loads, which could result
in loss of structural integrity of the wing attachment points.
DATES: This AD becomes effective May 12, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of May 12, 2006.
ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov
or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this 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:
Examining the Docket
You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Boeing
transport category airplanes. That NPRM was published in the Federal
Register on January 25, 2006 (71 FR 4069). That NPRM proposed to
require determining if the terminal fittings of the spars of the wings
are made of 7079 aluminum alloy material. For any positive finding, the
NPRM proposed to require doing repetitive inspections for cracks and
corrosion of all exposed surfaces of the terminal fitting bores; doing
repetitive inspections for cracks, corrosion, and other surface
defects, of all exposed surfaces, including the flanges, of the
terminal fitting; applying corrosion inhibiting compound to the
terminal fittings; and repairing or replacing any cracked, corroded, or
defective part with a new part. The NPRM also proposed to provide an
optional terminating action for the repetitive inspections.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received. The
commenter, Boeing, supports the NPRM.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD as proposed.
Interim Action
This AD is considered to be interim action. The inspection reports
that are required by this AD will enable the manufacturer to obtain
better insight into the extent of the cracking and corrosion of the
terminal fittings of the front and rear spars of the wings in the
fleet, and to develop additional action if necessary to address the
unsafe condition. If additional action is identified, we may consider
further rulemaking.
Costs of Compliance
There are about 302 airplanes of the affected design in the
worldwide fleet. This AD will affect about 157 airplanes of U.S.
registry. The determination of forging number/material identification
will take about 4 work hours per airplane, at an average labor rate of
$65
[[Page 17697]]
per work hour. Based on these figures, the estimated cost of the AD for
U.S. operators is $40,820, or $260 per airplane.
Accomplishing the fluorescent dye penetrant and detailed
inspections, if required, will take about 16 work hours per airplane,
at an average labor rate of $65 per work hour. Based on these figures,
we estimate the cost of the inspections to be $1,040 per airplane, per
inspection cycle.
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 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, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2006-07-17 Boeing: Amendment 39-14544. Docket No. FAA-2006-23672;
Directorate Identifier 2005-NM-237-AD.
Effective Date
(a) This AD becomes effective May 12, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 727, 727C, 727-100, 727-
100C, and 727-200 series airplanes, certificated in any category; as
identified in Boeing Alert Service Bulletin 727-57A0185, Revision 1,
dated November 3, 2005.
Unsafe Condition
(d) This AD results from reports of cracking of the terminal
fittings of the front and rear spars of the wings. We are issuing
this AD to detect and correct stress-corrosion cracking of the
terminal fittings, which could result in the failure of one of the
terminal fitting connections. Such a failure, combined with a
similar failure of one of the other three terminal fittings, could
result in the inability of the airplane structure to carry fail-safe
loads, which could result in loss of structural integrity of the
wing attachment points.
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.
Determination of Type of Terminal Fittings, Repetitive
Inspections, and Corrective Actions
(f) Within 24 months after the effective date of this AD,
determine if the terminal fittings of the front and rear spars of
the wings are made of 7079 aluminum alloy material by either
inspecting the forging number or doing a conductivity test, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 727-57A0185, Revision 1, dated November 3, 2005.
(1) If the forging number is that identified in Table 1 of this
AD, or if the terminal fitting material is not made of 7079 aluminum
alloy: No further action is required by this AD for that terminal
fitting only.
Table 1.--Forging Numbers of Terminal Fittings Not Made of 7079 Aluminum
Alloy
------------------------------------------------------------------------
Forging number of terminal fittings Location
------------------------------------------------------------------------
(i) 65-16214-3............................ Rear spar of left wing.
(ii) 65-16213-3........................... Front spar of left wing.
(iii) 65-16214-4.......................... Rear spar of right wing.
(iv) 65-16213-4........................... Front spar of right wing.
------------------------------------------------------------------------
(2) If any forging number other than those identified in Table 1
of this AD is found, or if any forging material is made of 7079
aluminum alloy, or if the material cannot be determined: Within 24
months after the effective date of this AD, do the inspections
specified in Table 2 of this AD and apply corrosion inhibiting
compound (CIC) to the terminal fittings, and before further flight,
repair or replace any cracked, corroded, or defective part found
during the inspections. Repeat the inspections thereafter at
intervals not to exceed 60 months for the first two repeat
intervals, and then thereafter at intervals not to exceed 30 months.
Do the inspections, application of CIC, and repair in accordance
with the service bulletin, except as provided by paragraphs (h) and
(i) of this AD. Do the replacement in accordance with paragraph (g)
of this AD.
Table 2.--Inspections
------------------------------------------------------------------------
Do-- For-- Of--
------------------------------------------------------------------------
(i) A fluorescent dye penetrant Cracks and All exposed
inspection. corrosion. surfaces of the
terminal fitting
bores.
(ii) A detailed inspection...... Cracks, corrosion, All exposed
and other surface surfaces,
defects. including the
flanges, of the
terminal fitting.
------------------------------------------------------------------------
[[Page 17698]]
Optional Terminating Action
(g) Replacement of any terminal fitting of the front and rear
spars of the wings with a new terminal fitting not made of 7079
aluminum alloy, in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA, ends the
repetitive inspections required by paragraph (f)(2) of this AD for
that terminal fitting only. For the replacement to be approved by
the Manager, Seattle ACO, as required by this paragraph, the
Manager's approval letter must specifically refer to this AD.
Exception to Service Information
(h) Where the service bulletin specifies to contact Boeing for
appropriate action: Before further flight, repair the cracked,
corroded, or defective part using a method approved in accordance
with the procedures specified in paragraph (l) of this AD, or
replace in accordance with paragraph (g) of this AD.
(i) Although the note in paragraph 3.B.7. of the service
bulletin specifies procedures for a fluorescent dye penetrant
inspection of the body fitting bore and repair if necessary, those
procedures are not required by this AD.
Parts Installation
(j) As of the effective date of this AD, no person may install
any terminal fitting having forging number 65-16213-1/-2 or 65-
16214-1/-2, or install any terminal fitting material made of 7079
aluminum alloy, on any airplane.
Reporting
(k) Submit a report of the findings (both positive and negative)
of the initial inspection required by paragraph (f)(2) of this AD to
Boeing Commercial Airplanes, Attention: Manager, Airline Support,
P.O. Box 3707, Seattle, WA 98124-2207, at the applicable time
specified in paragraph (k)(1) or (k)(2) of this AD. The report must
include the operator's name, inspection results, a detailed
description of any discrepancies found, the airplane serial number,
and the number of flight cycles and flight hours on the airplane.
Under the provisions of the Paperwork Reduction Act of 1980 (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements contained in this
AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection was done after the effective date of this
AD: Submit the report within 30 days after the inspection.
(2) If the inspection was accomplished prior to the effective
date of this AD: Submit the report within 30 days after the
effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(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.
Material Incorporated by Reference
(m) You must use Boeing Alert Service Bulletin 727-57A0185,
Revision 1, dated November 3, 2005, to perform the actions that are
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register approved the incorporation by reference of
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at http://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Issued in Renton, Washington, on March 24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-3197 Filed 4-6-06; 8:45 am]
BILLING CODE 4910-13-P