[Federal Register Volume 76, Number 55 (Tuesday, March 22, 2011)]
[Proposed Rules]
[Pages 15864-15867]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-6613]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0254; Directorate Identifier 2010-NM-180-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 737-600, -700,
-700C, -800, -900, and -900ER Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. For certain airplanes, this proposed AD would
require a one-time inspection for damage of the hydraulic actuator rod
ends and actuator attach fittings on the thrust reversers, and repair
or replacement if necessary. For all airplanes, this proposed AD also
would require repetitive inspections for damage of the hydraulic
actuator rod ends, attach bolts, and nuts; repetitive inspections for
damage of fitting assemblies, wear spacers, and actuator attach
fittings on the thrust reverser; repetitive measurements of the wear
spacer; and corrective actions if necessary. This proposed AD was
prompted by in-service damage of the attachment fittings for the thrust
reverser actuator. We are proposing this AD to detect and correct such
damage, which could result in actuator attach fitting failure, loss of
the thrust reverser auto restow function, and consequent loss of
control of the airplane.
DATES: We must receive comments on this proposed AD by May 6, 2011.
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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; phone: 206-
544-5000, extension 1; fax: 206-766-5680; e-mail: [email protected];
Internet: https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221.
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
[[Page 15865]]
(phone: 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Chris R. Parker, Aerospace Engineer,
Propulsion Branch, ANM-140S, Seattle Aircraft Certification Office
(ACO), FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356;
phone: 425-917-6496; fax: 425-917-6590; e-mail: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2011-0254;
Directorate Identifier 2010-NM-180-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
We have received a report indicating that the attachment fittings
for the thrust reverser actuator have shown in-service wear damage.
While in the stowed position, the actuator is locked and is in tension.
The tensile load applied by the locking screw causes the hydraulic
actuator rod end to rotate. As the hydraulic actuator rod end rotates,
wear occurs to the bushings in the actuator attach fitting. The
bushings continue to wear until there is contact directly between the
hydraulic actuator rod end and the attach fitting. This condition, if
not detected and corrected, could result in actuator attach fitting
failure and loss of the thrust reverser auto restow function. Loss of
the thrust reverser auto restow function removes one of the three
primary levels of protection against an uncommanded thrust reverser
deployment. An uncommanded thrust reverser deployment could result in
loss of airplane control.
Relevant Service Information
We reviewed Boeing Special Attention Service Bulletin 737-78-1083,
dated June 30, 2010. For Group 1 airplanes, this service bulletin
specifies a one-time detailed inspection to detect damage (i.e., wear,
cracks, nicks, dents, and scratches) of the hydraulic actuator rod ends
and the actuator attach fittings on the right and left thrust
reversers.
For airplanes on which damage is found on a hydraulic actuator rod
end, this service bulletin specifies replacing of the hydraulic
actuator rod end assembly with a new hydraulic actuator rod end
assembly.
For airplanes on which no damage is found on an actuator attach
fitting, this service bulletin specifies installing of a new spacer.
For damage found on an actuator attach fitting that is within stated
repair limits, this service bulletin specifies repairing the actuator
attach fitting and installing a new spacer. For damage that exceeds the
repair limits of the actuator attach fitting, this service bulletin
specifies replacing the actuator attach fitting with a new actuator
fitting.
For both Group 1 and Group 2 airplanes, this service bulletin
describes procedures for repetitive inspections for damage (as
specified in each inspection that follows), repetitive measurements,
and corrective actions if necessary. The inspections and measurement
include the following:
A general visual inspection for cracks, nicks, dents, and
scratches of the fitting assembly
A detailed inspection for tears, holes, and disbonds of
the wear spacer
A measurement of the thickness of the wear spacer
A detailed inspection for surface damage of the attach
fitting
A general visual inspection for damage (i.e. missing,
cracked, or bent parts) of the rod end, attach bolt, and nut
The corrective actions include replacing spacers with new spacers,
repairing attach fittings, replacing attach fittings with new attach
fittings, replacing the rod end, attach bolt, and nuts with a new
actuator rod end assembly.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
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
Information.''
Differences Between the Proposed AD and the Service Information
Appendix A of Boeing Special Attention Service Bulletin 737-78-
1083, dated June 30, 2010, specifies a general visual inspection for
cracks, nicks, dents, and scratches of the fitting assembly. We have
determined that this inspection is accomplished during the detailed
inspections specified in Appendix A of Boeing Special Attention Service
Bulletin 737-78-1083, dated June 30, 2010.
Appendix A of Boeing Special Attention Service Bulletin 737-78-
1083, dated June 30, 2010, specifies to replace missing, cracked, and
bent rod ends, attach bolts, and nuts, but does not specify replacement
parts and how to replace the affected part. This proposed AD would
require replacing missing, cracked, and bent rod ends, attach bolts,
and nuts with new parts in accordance with a method approved by the
FAA.
Costs of Compliance
We estimate that this proposed AD will affect 1,070 airplanes of
U.S. registry.
We estimate the following costs to comply with this proposed AD:
Estimated costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
One-time detailed inspection and 28 work-hours x $85 $68 $2,448.............. $2,080,800.
installation (Group 1: 850 per hour = $2,380.
airplanes).
General visual and detailed 23 work-hours x $85 0 $1,955 per $2,091,850 per
inspections (Group 1 and 2 per hour = $1,955 inspection cycle. inspection cycle.
airplanes). per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
[[Page 15866]]
We estimate the following costs to do any necessary repairs or
replacements that would be required based on the results of the
proposed inspection. These on-condition costs are based on all the
thrust reverser attachment fittings needing repair or replacement. We
have no way of determining the number of aircraft that might need these
repairs or replacements.
On-Condition Costs
------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
------------------------------------------------------------------------
Attach fitting replacement... 75 work-hours x $10,850 $17,225
$85 per hour =
$6,375.
------------------------------------------------------------------------
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
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
airworthiness directive (AD):
The Boeing Company: Docket No. FAA-2011-0254; Directorate Identifier
2010-NM-180-AD.
Comments Due Date
(a) We must receive comments by May 6, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 737-600, -700, -
700C,-800, -900, and -900ER series airplanes, certificated in any
category, as identified in Boeing Special Attention Service Bulletin
737-78-1083, dated June 30, 2010.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 78, Exhaust.
Unsafe Condition
(e) This AD was prompted by in-service damage of the attachment
fittings for the thrust reverser actuator. We are issuing this AD to
detect and correct such damage, which could result in actuator
attach fitting failure, loss of the thrust reverser auto restow
function, and consequent loss of control of the airplane.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Inspection and Repair: Group 1 Airplanes
(g) For Group 1 airplanes, as identified in Boeing Special
Attention Service Bulletin 737-78-1083, dated June 30, 2010: At the
compliance time specified in paragraph (g)(1) or (g)(2) of this AD,
whichever is later, perform a one-time detailed inspection to detect
wear, cracks, nicks, dents, and scratches of the hydraulic actuator
rod ends and actuator attach fittings on the thrust reversers, in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-78-1083, dated June 30, 2010.
(1) Within 7,500 flight hours after the effective date of this
AD.
(2) Before the accumulation of 15,000 total flight cycles or
30,000 total flight hours, whichever occurs first.
(h) If any wear, crack, nick, dent, or scratch of any hydraulic
actuator rod end is found during the inspection required by
paragraph (g) of this AD: Before further flight, replace the
affected hydraulic actuator rod end assembly with a new hydraulic
actuator rod end assembly, in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 737-78-
1083, dated June 30, 2010.
(i) If no wear, cracks, nicks, dents, and scratches of any
actuator attach fittings are found during the inspection required by
paragraph (g) of this AD: Before further flight, install new wear
spacers on the affected actuator attach fitting, in accordance with
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-78-1083, dated June 30, 2010.
(j) If any wear, crack, nick, dent, or scratch of any actuator
attach fitting is found during the inspection required by paragraph
(g) of this AD, and is less than 0.005 inch in depth: Before further
flight, repair the affected actuator attach fitting and install the
new wear spacer, in accordance with the Accomplishment Instructions
of Boeing Special Attention Service Bulletin 737-78-1083, dated June
30, 2010.
(k) If any wear, crack, nick, dent, or scratch of any actuator
attach fitting is found during the inspection required by paragraph
(g) of this AD, and is 0.005 inch or greater in depth: Before
further flight, replace the actuator attach fitting with a new
actuator attach fitting, in accordance with the Accomplishment
Instructions of Boeing
[[Page 15867]]
Special Attention Service Bulletin 737-78-1083, dated June 30, 2010.
Repetitive Inspections and Corrective Actions
(l) For Group 1 airplanes, as identified in Boeing Special
Attention Service Bulletin 737-78-1083, dated June 30, 2010: Within
7,500 flight hours after accomplishing the requirements of paragraph
(g) of this AD, do the actions specified in paragraphs (l)(1),
(l)(2), (l)(3), and (l)(4) of this AD. Repeat the actions thereafter
at intervals not to exceed 7,500 flight hours.
(1) Do a detailed inspection for tears, holes, and disbonds of
the wear spacer, in accordance with Appendix A of Boeing Special
Attention Service Bulletin 737-78-1083, dated June 30, 2010. If any
tear, hole, or disbond is found, before further flight, replace the
spacer with a new spacer, in accordance with Appendix A of Boeing
Special Attention Service Bulletin 737-78-1083, dated June 30, 2010.
(2) Measure the thickness of the wear spacer in accordance with
Appendix A of Boeing Special Attention Service Bulletin 737-78-1083,
dated June 30, 2010. If the thickness is less than 0.020 inch,
before further flight, replace the spacer with a new spacer, in
accordance with Appendix A of Boeing Special Attention Service
Bulletin 737-78-1083, dated June 30, 2010.
(3) Do a detailed inspection for surface damage of the attach
fitting, in accordance with Appendix A of Boeing Special Attention
Service Bulletin 737-78-1083, dated June 30, 2010.
(i) If the surface damage is less than 0.005 inch depth, before
further flight, repair the attach fitting, in accordance with
Appendix A of Boeing Special Attention Service Bulletin 737-78-1083,
dated June 30, 2010.
(ii) If the surface damage is 0.005 inch or greater in depth,
before further flight, replace the attach fitting with a new attach
fitting, in accordance with Appendix B of Boeing Special Attention
Service Bulletin 737-78-1083, dated June 30, 2010.
(4) Do a general visual inspection for damage (i.e. wear,
missing, cracked, or bent parts) of the rod end, attach bolt, and
nut, in accordance with Appendix A of Boeing Special Attention
Service Bulletin 737-78-1083, dated June 30, 2010. If any damage is
found, before further flight, replace the affected part with a new
part in accordance with a method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA.
Group 2 Inspection and Repair
(m) For Group 2 airplanes, as identified in Boeing Special
Attention Service Bulletin 737-78-1083, dated June 30, 2010: Within
12 months after the effective date of this AD, perform the actions
required in paragraph (l) of this AD. Repeat the actions thereafter
at intervals not to exceed 7,500 flight hours.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Seattle Aircraft Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the ACO, send it to the attention of the
person identified in the Related Information section of this AD.
Information may be e-mailed to [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
Related Information
(o) For more information about this AD, contact Chris R. Parker,
Aerospace Engineer, Propulsion Branch, ANM-140S, Seattle Aircraft
Certification Office (ACO), FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; phone: 425-917-6496; fax: 425-917-6590; e-
mail: [email protected].
(p) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; phone:
206-544-5000, extension 1; fax: 206-766-5680;e-mail:
[email protected]; Internet:https://www.myboeingfleet.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, the FAA, 1601 Lind Avenue, SW.,
Renton, Washington. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on March 14, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-6613 Filed 3-21-11; 8:45 am]
BILLING CODE 4910-13-P