[Federal Register: January 25, 2006 (Volume 71, Number 16)]
[Proposed Rules]
[Page 4069-4072]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25ja06-23]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23672; Directorate Identifier 2005-NM-237-AD]
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: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing transport category airplanes. This proposed AD would
require determining if the terminal fittings of the spars of the wings
are made of 7079 aluminum alloy material. For any positive finding, the
proposed AD would 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. This proposed AD also provides for an
optional terminating action for the repetitive inspections. This
proposed AD results from reports of cracking of the terminal fittings
of the spars of the wings. We are proposing 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: We must receive comments on this proposed AD by March 13, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for the service information identified in this
proposed 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:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
23672; Directorate Identifier 2005-NM-237-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.
Examining the Docket
You may 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
[[Page 4070]]
(800) 647-5227) is located on the plaza level of the Nassif Building at
the DOT street address stated in the ADDRESSES section. Comments will
be available in the AD docket shortly after the Docket Management
System receives them.
Discussion
We have received reports of cracking of the terminal fittings of
the front and rear spars of the wings. The affected terminal fittings
were made from a 7079-T6 aluminum forging. This material is known to be
susceptible to stress-corrosion cracking. This condition, if not
detected and corrected, 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.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 727-57A0185,
Revision 1, dated November 3, 2005. The service bulletin describes
procedures for determining 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. For
any case where the terminal fitting is determined to be made of 7079
aluminum alloy material or where the material cannot be determined, the
service bulletin describes procedures for doing repetitive fluorescent
dye penetrant inspections for cracks and corrosion of all exposed
surfaces of the terminal fitting bores; doing repetitive detailed
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 any cracked, corroded, or defective part or contacting Boeing
if necessary.
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, except as discussed under
``Differences Between the Proposed AD and Service Bulletin.'' In
addition, the proposed AD would provide for an optional terminating
action for the repetitive inspections. The proposed AD also would
require sending the initial inspection results to Boeing.
Differences Between the Proposed AD and Service Bulletin
The service bulletin 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.
In paragraph 1.E., the service bulletins states, ``Contact Boeing
for replacement of the fitting with a fitting not made from 7079
aluminum alloy. Replacement of the fitting is considered terminating
action for that fitting only.'' However, the Accomplishment
Instructions of the service bulletin do not contain any procedures for
accomplishing this replacement. Therefore, this proposed AD specifies
that the optional replacement be done in accordance with a method
approved by the Manager, Seattle Aircraft Certification Office.
Interim Action
This proposed 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 proposed AD would affect about 157 airplanes of
U.S. registry. The proposed determination of forging number/material
identification would take about 4 work hours per airplane, at an
average labor rate of $65 per work hour. Based on these figures, the
estimated cost of the proposed 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 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:
[[Page 4071]]
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-2006-23672; Directorate Identifier 2005-NM-
237-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by March 13,
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 Not Made of 7079 Aluminum Alloy
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Forging No. of terminal fittings Location
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(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.
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(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
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Do-- For-- Of--
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(i) A fluorescent dye Cracks and All exposed surfaces
penetrant inspection. corrosion. of the terminal
fitting bores.
(ii) A detailed inspection.... Cracks, All exposed surfaces,
corrosion, and including the
other surface flanges, of the
defects. terminal fitting.
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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 Airplane Group, 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
[[Page 4072]]
certification basis of the airplane, and the approval must
specifically refer to this AD.
Issued in Renton, Washington, on January 17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-903 Filed 1-24-06; 8:45 am]
BILLING CODE 4910-13-P