[Federal Register: October 30, 2008 (Volume 73, Number 211)]
[Proposed Rules]
[Page 64568-64571]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30oc08-17]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1118; Directorate Identifier 2007-NM-318-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-600, -700, -700C, -
800, and -900 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 supersede an existing airworthiness
directive (AD) that applies to all Boeing Model 737-600, -700, -700C, -
800, and -900 series airplanes. The existing AD currently requires
reviewing the airplane maintenance records to determine whether an
engine has been removed from the airplane since the airplane was
manufactured. For airplanes on which an engine has been removed, the
existing AD also requires an inspection of the aft engine mount to
determine if the center link assembly is correctly installed, and
follow-on actions if necessary. This proposed AD would require the same
actions for airplanes on which the engine has not been previously
removed. This proposed AD results from reports indicating that
operators found that the center link assembly for the aft engine mount
was reversed on several airplanes that had not had an engine removed
since delivery. We are proposing this AD to prevent increased
structural loads on the aft engine mount, which could result in failure
of the aft engine mount and consequent separation of the engine from
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: Allen Rauschendorfer, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6432; 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-2008-1118;
Directorate Identifier 2007-NM-318-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 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
On January 21, 2003, we issued AD 2003-03-01, amendment 39-13025
(68 FR 4367, January 29, 2003), for all Boeing Model 737-600, -700, -
700C, -800, and -900 series airplanes. That AD requires reviewing the
airplane maintenance records to determine whether an engine has been
removed from the airplane since the airplane was manufactured. For
airplanes on which an engine has been removed, that AD requires an
inspection of the aft engine mount to determine if the center link
assembly is correctly installed, and follow-on actions if necessary.
That AD resulted from reports indicating that operators found that the
center link assembly for the aft engine mount was reversed on several
airplanes. We issued that AD to prevent increased structural loads on
the aft engine mount, which could result in failure of the aft engine
mount and consequent separation of the engine from the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2003-03-01, the manufacturer informed us that it
is possible that some center links were incorrectly installed in an aft
engine mount before the airplane was delivered. In AD 2003-03-01
inspection of the aft engine mounts was required only for airplanes
that had an engine change after the airplane was delivered to the
operator. The inspection is now necessary for all airplanes, line
numbers 1 through 1277 inclusive.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-71A1462,
Revision 3, dated May 20, 2004. The procedures in Revision 3 of the
service bulletin are essentially the same as those in Boeing Alert
Service Bulletin 737-71A1462, Revision 1, dated November 7, 2002. We
referred to Revision 1 of the service bulletin as the appropriate
source of service information for accomplishing the actions required by
AD 2003-03-01. However, Revision 3 of the service bulletin also
specifies inspecting to determine if the center link assembly is
installed correctly on any installed engine that has not been removed
from
[[Page 64569]]
the airplane since the airplane's delivery. Revision 3 of the service
bulletin also specifies repeating the inspection during each subsequent
engine change for each aft engine mount. Finally, Revision 3 also
specifies that adding permanent part marks on the center link assembly
and the hanger fitting ends the need for the repetitive inspections.
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 develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2003-03-01 and would retain the requirements of the
existing AD. This proposed AD would also require the same actions for
airplanes on which the engine has not been previously removed. This
proposed AD would also require accomplishing the actions specified in
the service bulletin described previously, except as discussed under
``Difference Between the Proposed AD and the Service Bulletin.''
Difference Between the Proposed AD and the Service Bulletin
Boeing Alert Service Bulletin 737-71A1462, Revision 3 specifies
contacting the part manufacturer (CFMI) for more instructions if damage
is found to the engine mounting lugs and the adjacent engine turbine
rear frame. (Damage includes cracking, yielding, buckling, and wear.)
However, 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
(DOA) Organization whom we have authorized to make those findings.
Clarification of Certain Actions
Revision 3 of the service bulletin specifies repeating the
inspection during each subsequent engine change for each aft engine
mount. This proposed AD does not specify a repetitive inspection but
instead specifies in paragraph (n), ``Parts Installation,'' that no
person may install an engine on any airplane unless the center link
assembly of the aft engine mount is found to be installed correctly.
Revision 3 of the service bulletin also specifies that adding
permanent part marks on the center link assembly and the hanger fitting
ends the need for the repetitive inspections. As noted above, this
proposed AD would not include a repetitive inspection requirement. In
addition, because the affected parts are rotable, the repetitive
inspections referred to in the service bulletin would be terminated
only as long as the engine stays on the airplane.
Changes to Existing AD
This proposed AD would retain the requirements of AD 2003-03-01.
Since AD 2003-03-01 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
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Corresponding requirement in
Requirement in AD 2003-03-01 this proposed AD
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Paragraph (a)........................... Paragraph (f).
Paragraph (b)........................... Paragraph (g).
Paragraph (c)........................... Paragraph (h).
Paragraph (d)........................... Paragraph (i).
Paragraph (e)........................... Paragraph (m).
Paragraph (f)........................... Paragraph (n).
------------------------------------------------------------------------
We have also removed Note 1 of the existing AD and re-numbered
subsequent notes accordingly. We have also revised Note 2 and Note 3 of
the existing AD (Note 1 and Note 2 of this proposed AD) to provide a
more up-to-date definition of a general visual inspection and a
detailed inspection.
Boeing Commercial Airplanes has received a DOA. We have revised
paragraph (i) of this AD (paragraph (d) of AD 2003-03-01) to delegate
the authority to approve an alternative method of compliance for any
repair required by this proposed AD to an Authorized Representative for
the Boeing Commercial Airplanes DOA rather than a Designated
Engineering Representative (DER). We have also simplified paragraph (i)
of this AD by referring to the ``Alternative Methods of Compliance
(AMOCs)'' paragraph (o) of this proposed AD for repair methods, which
includes a reference to the DOA.
Costs of Compliance
There are about 1,277 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 500 airplanes of
U.S. registry. The average labor rate is $80 per work hour. The
following table provides the estimated costs for U.S. operators to
comply with this proposed AD.
Estimated Costs
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Cost per
Action Work hours Parts airplane Fleet cost
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Maintenance records review (required by AD 2003-03-01)...... 1 $0 $80 $40,000
Inspection for correct installation of center link assembly 1 0 80 40,000
(new proposed action)......................................
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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 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.
[[Page 64570]]
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, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-13025 (68 FR 4367, January 29, 2003) and adding
the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2008-1118; Directorate Identifier 2007-NM-
318-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by December
15, 2008.
Affected ADs
(b) This AD supersedes AD 2003-03-01.
Applicability
(c) This AD applies to all Boeing Model 737-600, -700, -700C, -
800, and -900 series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from reports indicating that operators found
that the center link assembly for the aft engine mount was reversed
on several airplanes that had not had an engine removed since
delivery. We are issuing this AD to prevent increased structural
loads on the aft engine mount, which could result in failure of the
aft engine mount and consequent separation of the engine from the
airplane.
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.
Restatement of the Requirements of AD 2003-03-01
Review of Maintenance Records
(f) Within 90 days after February 13, 2003 (the effective date
of AD 2003-03-01), review the airplane maintenance records to
determine whether either engine has been removed since the
airplane's date of manufacture. If neither engine has been removed
since the airplane's date of manufacture, no further action is
required by this paragraph; however paragraph (n) of this AD
continues to apply.
Inspection To Determine if Center Link Assembly Is Installed Correctly
(g) For any installed engine that is found to have been removed
from the airplane since the airplane's date of manufacture: Within
90 days after February 13, 2003, do a one-time general visual
inspection to determine if the center link assembly of the aft
engine mount is installed correctly, per the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-71A1462, Revision
1, dated November 7, 2002; or Revision 3, dated May 20, 2004. If the
center link assembly is installed correctly, as specified in the
service bulletin, no further action is required by paragraph (g),
(h), or (i) of this AD for that engine; however paragraph (n) of
this AD continues to apply.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
Follow-on and Corrective Actions
(h) For any center link assembly that is found installed
incorrectly during the inspection required by paragraph (g) of this
AD: Before further flight, do the actions in paragraphs (h)(1),
(h)(2), and (h)(3) of this AD, per the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-71A1462, Revision 1, dated
November 7, 2002; or Revision 3, dated May 20, 2004; except that it
is not necessary to submit a report of findings to the airplane
manufacturer.
(1) Remove the center link assembly and install it correctly.
(2) Perform a detailed inspection of the engine mounting lugs
and engine turbine rear frame for cracking, yielding, buckling, or
wear damage.
(3) Perform a detailed inspection of the hardware for the aft
engine mount; including the center link assembly, right link
assembly, aft mount hanger assembly, and link pins; for cracking,
yielding, buckling, or wear damage.
Note 2: 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
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repair
(i) If any cracking, yielding, buckling, or wear damage is found
during the inspections required by paragraphs (h)(2) and (h)(3) of
this AD: Before further flight, replace the discrepant part with a
new or serviceable part, or repair in accordance with a method
approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA; or using a method approved in accordance with the
procedures specified in paragraph (o) of this AD.
New Requirements of This AD
Inspection of Engines That Have Not Been Removed
(j) For all airplanes identified in Boeing Alert Service
Bulletin 737-71A1462, Revision 3, dated May 20, 2004: For any
installed engine that has not been removed from the airplane since
the airplane's date of manufacture, within 90 days after the
effective date of this AD, do a detailed inspection to determine if
the center link assembly of the aft engine mount is installed
correctly, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-71A1462, Revision 3, dated May 20,
2004.
Follow-on and Corrective Actions
(k) For any center link assembly that is found installed
incorrectly during any inspection required by paragraph (j) of this
AD: Before further flight, do the actions required by paragraphs
(k)(1), (k)(2), and (k)(3) of this AD, per the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-71A1462, Revision
3, dated May 20, 2004, except that it is not necessary to submit a
report of findings to the airplane manufacturer.
(1) Remove the center link assembly and install it correctly.
(2) Perform a detailed inspection of the engine mounting lugs
and engine turbine rear frame for cracking, yielding, buckling, or
wear damage.
(3) Perform a detailed inspection of the hardware for the aft
engine mount; including the center link assembly, right link
assembly, aft mount hanger assembly, and link pins; for cracking,
yielding, buckling, or wear damage.
Repair
(l) If any cracking, yielding, buckling, or wear damage is found
during the inspections required by paragraphs (k)(2) and (k)(3) of
this AD, and Boeing Alert Service Bulletin 737-71A1462, Revision 3,
dated May 20, 2004, specifies to contact Boeing or the part
[[Page 64571]]
manufacturer: Before further flight, replace the discrepant part
(e.g., parts with cracking, yielding, buckling, and wear damage)
with a new or serviceable part, or repair using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD.
Credit for Actions Done Using Previous Service Information
(m) Inspections and corrective actions done before the effective
date of this AD in accordance with a service bulletin listed in
Table 1 of this AD are acceptable for compliance with the
corresponding requirements of this AD.
Table 1--Previous Service Bulletins
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Boeing Alert Service Bulletin Revision Date
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737-71A1462..................... Original....... Aug. 29, 2002.
737-71A1462..................... 1.............. Nov. 7, 2002.
737-71A1462..................... 2.............. May 29, 2003.
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Parts Installation
(n) As of the effective date of this AD, no person may install
an engine on any airplane unless the inspections specified in
paragraph (g) or (j) of this AD are accomplished and the center link
assembly of the aft engine mount is found to be installed correctly.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, Seattle Aircraft Certification Office (ACO)
FAA, ATTN: Allen Rauschendorfer, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601
Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6432; 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. E8-25903 Filed 10-29-08; 8:45 am]
BILLING CODE 4910-13-P