Airworthiness Directives; The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER Series Airplanes, 59167-59170 [2010-24175]
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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Proposed Rules
emcdonald on DSK2BSOYB1PROD with PROPOSALS
integrated in a revised 10 CFR Part 20.
However, some challenges are expected
in modifying some of the regulatory
provisions of Appendix I to 10 CFR Part
50. The following identifies specific
provisions of Appendix I to 10 CFR Part
50 and 10 CFR Part 20 regulations that
may need to be reviewed and updated,
as warranted:
Provisions: 4.1: Numerical design
objectives of 10 CFR Part 50, Appendix I for
liquid and gaseous effluents—The revision
would retain the current numerical dose
criteria, but would redefine doses as effective
dose (ED) or TED for consistency with ICRP
Publication 103 dosimetry concepts in a
revised 10 CFR Part 20, or as TEDE with the
current 10 CFR Part 20 (ICRP Publications 26
and 30) if 10 CFR Part 20 were not realigned
with ICRP Publication 103. The update
would necessitate a revision of dose
calculation methods described in Regulatory
Guide 1.109 and associated computer codes.
4.2: Organ numerical design objectives of
10 CFR Part 50, Appendix I for liquid and
gaseous effluents—The revision would assess
whether there is still a need to report doses
separately for organs since this would not be
necessary if ICRP Publication 103 or ICRP
Publications 26 and 30 were adopted. The
assessment would consider the provisions of
Sections II and III of Appendix I to 10 CFR
Part 50 on doses associated with radioiodine
in situations where releases might be
dominated by the presence of noble gases
and radioiodine, resulting in potentially
significant skin and thyroid doses. The
assessment would also consider the need to
revise the scope of thyroid dose contributors
to include radionuclides present as vapor
(tritium) and gases (e.g., 14C in inorganic and
organic forms) in addition to radioiodine and
particulates.
4.3: Annual gamma and beta air dose for
gaseous effluents—The gamma and beta dose
criteria characterize an absorbed dose rate in
air, expressed in mrad/year, while the
balance of the design objectives are expressed
in mrem/year for the total body and organs.
The revision would assess the need to still
report gamma and beta absorbed air dose
results based on a review of historical
gaseous effluent releases and doses from
operating PWR and BWR plants. The revision
might consider dropping that requirement
altogether, or alternatively, converting the
design objective to an ED or TED dose for a
receptor assumed to be located at the site
boundary.
4.4: Light-Water-Cooled Reactor Provisions
of Appendix I to 10 CFR Part 50—The
revision would consider whether there is a
need to expand current regulatory provisions
for design certifications and new reactor
applications involving other types of reactor
technologies. Such new technologies might
include new types of reactor fuels and
modular reactor technologies, e.g., high
temperature gas-cooled reactors, molten-salt
or lead-cooled reactors, and breeder reactors.
4.5: Compliance with Requirements for
‘‘Licensed Operation’’ under 10 CFR Part 20—
The revision would consider the need to
expand provisions describing compliance
requirements for ‘‘licensed operation’’ for
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sites with two or more licensed entities
contributing to and radiation exposures to a
single offsite dose receptor under Parts
20.1301(a)(1) and 20.1302(a) and (b). The
expanded provisions would identify
acceptable methods in the regulation or
guidance for apportioning radioactive
effluent releases and doses between two or
more licensed entities. The discussion would
also consider compliance with EPA
regulations of 40 CFR Part 190 as
implemented under 10 CFR Part 20.1301(e).
Questions: Q4–1: Given the above
summary descriptions of the provisions of 10
CFR Part 50, Appendix I that might be
considered for possible revision, should the
NRC evaluate all provisions described above,
or focus instead only on those necessary to
align 10 CFR Part 50, Appendix I regulations
with ICRP Publication 103 if 10 CFR Part 20
were revised, or with ICRP Publication 26
and 30 if 10 CFR Part 20 were not revised?
Q4–2: Given the above, are there any
significant impacts in the implementation of
revised 10 CFR Part 50, Appendix I
regulations that the NRC should consider if
it were to proceed with a rulemaking?
Q4–3: If significant impacts in the
implementation of revised 10 CFR Part 50,
Appendix I regulations are envisioned, what
types of issues should the NRC evaluate and
consider in revising 10 CFR Part 50,
Appendix I regulations?
Dated at Rockville, Maryland, this 20th day
of September, 2010.
For the Nuclear Regulatory Commission.
Mark Thaggard,
Deputy Director, Division of
Intergovernmental Liaison and Rulemaking,
Office of Federal and State Materials and
Environmental Management Program.
[FR Doc. 2010–24137 Filed 9–24–10; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0858; Directorate
Identifier 2010–NM–183–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER Series
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Model 737–600, –700, –700C, –800,
–900, and –900ER series airplanes. This
proposed AD would require modifying
the thrust reverser inner walls,
inspecting for damage of the upper and
SUMMARY:
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59167
lower inner wall insulation blankets,
measuring the electrical conductivity on
the aluminum upper compression pads
2 and 3 as applicable, inspecting for
discrepancies of the inner wall of the
thrust reverser, and corrective actions if
necessary. This proposed AD would
also require, for certain airplanes, doing
various concurrent actions (including
replacing the inner wall blanket
insulation, installing updated fullauthority digital electronic control
software, and modifying the thrust
reverser inner wall and insulation
blankets). This proposed AD results
from reports of heat damage to the inner
wall of the thrust reversers. We are
proposing this AD to detect and correct
such heat damage, which could result in
separation of adjacent components and
consequent structural damage to the
airplane, damage to other airplanes, and
injury to people on the ground.
DATES: We must receive comments on
this proposed AD by November 12,
2010.
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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 proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; 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.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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
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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Proposed Rules
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:
Chris Parker, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
425–917–6496; fax 425–917–6590.
SUPPLEMENTARY INFORMATION:
FAA–2010–0858; Directorate Identifier
2010–NM–183–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 https://
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.
Comments Invited
Discussion
We have received reports of heatrelated damage to the inner wall of the
thrust reverser. During an inspection of
a thrust reverser, one operator found
heat damage at different locations of the
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.
inner wall: At the top, in the area of the
number 2 and number 3 upper
compression pads, and at the lower aft
edge. A flight test at Boeing showed that
the temperatures applied to the inner
walls of the thrust reversers are too
high. Higher temperatures are due to hot
precooler air leakage between the inner
wall of the thrust reverser and the
insulation blankets and heat transfer
through the upper compression pad area
and the fireseal bracket support flange.
Heat damage to the thrust reverser inner
wall, if not corrected, could result in
separation of adjacent components and
consequent structural damage to the
airplane, damage to other airplanes, and
injury to people on the ground.
Relevant Service Information
We have reviewed the service
bulletins identified in the following
table.
SERVICE INFORMATION
Revision level
Date
Boeing Service Bulletin 737-78-1082 .......................................................................
Boeing Service Bulletin 737-78-1088 .......................................................................
Boeing Service Bulletin 737-78-1079 .......................................................................
Boeing Service Bulletin 737-78-1069 .......................................................................
Boeing Service Bulletin 737-78-1063 .......................................................................
CFM CFM56–7B Service Bulletin 73-0135 ..............................................................
emcdonald on DSK2BSOYB1PROD with PROPOSALS
Service Bulletin
Original ....................................................
Original ....................................................
2 ..............................................................
4 ..............................................................
2 ..............................................................
Original ....................................................
March 25, 2010.
May 12, 2010.
June 7, 2010.
June 16, 2005.
October 7, 1999.
March 30, 2007.
Boeing Service Bulletin 737–78–1082
describes procedures for modifying the
thrust reverser inner wall by drilling a
hole through the inner wall behind the
number 3 upper compression pad, and
installing a bushing, applying sealant to
areas of the insulation blankets, and
installing flange insulation assemblies at
the top aft edge of the upper insulation
blanket.
Boeing Service Bulletin 737–78–1088
describes procedures for the following:
• Detailed inspection for damage of
the engine side and inner wall side of
the upper and lower insulation blankets.
• Measurement of the electrical
conductivity on the aluminum upper
compression pads 2 and 3, as
applicable.
• Inspections for discrepancies of the
inner wall of the thrust reverser,
including an ultrasonic inspection of
the thrust reverser inner wall for
interplay delamination and skin-to-core
disbond.
• Detailed inspection, for certain
airplanes, of the thrust reverser inner
wall for signs of heat damage.
• Detailed inspection of the thrust
reverser inner wall for indications of
loose fasteners where the inner wall
attaches to the hinge beam and at the
fasteners for the compression pads.
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• Corrective actions, including
repairing or replacing damaged
insulation blankets and repairing the
thrust reverser inner wall (including
replacing loose fasteners and contacting
Boeing for a repair procedure), and
replacing any unserviceable
compression pad with a new one.
Boeing Service Bulletin 737–78–1079
describes procedures for essentially the
same actions (including inspections and
modification) specified in Boeing
Service Bulletins 737–78–1082 and
737–78–1088.
Boeing Service Bulletin 737–78–1082
also specifies the concurrent
accomplishment of the actions specified
in Boeing Service Bulletin 737–78–
1063: replacement of the inner wall
blanket insulation.
Boeing Service Bulletin 737–78–1082
also specifies the concurrent
accomplishment of the actions specified
in CFM CFM56–7B Service Bulletin 73–
0135: installation of updated fullauthority digital electronic control
(FADEC) software.
Boeing Service Bulletin 737–78–1088
specifies the concurrent
accomplishment of the actions specified
in Boeing Service Bulletin 737–78–
1069: modification of the thrust reverser
inner walls and insulation blankets. The
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modification involves installing
additional supports on the inner wall of
the thrust reverser for the attachment of
the insulation blankets, installing new
brackets to attach the forward edge of
the upper and lower insulation blankets,
installing additional attachment
grommets to the blankets, and sealing
the blankets at the forward edge of the
fan duct inner walls.
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of these same
type designs. This proposed AD would
require accomplishing the actions
specified in the service information
described previously, except as
discussed below.
Differences Between the Proposed AD
and Service Information
Although Boeing Service Bulletin
737–78–1088 specifies that operators
may contact the manufacturer for
disposition of certain repair conditions,
this proposed AD would require
operators to repair those conditions
using a method approved by the FAA.
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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Proposed Rules
Clarification of Certain Terminology
those parts or locations are
‘‘unserviceable.’’
Where Boeing Service Bulletin 737–
78–1088 refers to ‘‘unsatisfactory’’
findings, this proposed AD assumes
Costs of Compliance
We estimate that this proposed AD
would affect 710 airplanes of U.S.
registry. The following table provides
the estimated costs for U.S. operators to
comply with this proposed AD, at an
average labor rate of $85 per hour.
ESTIMATED COSTS
Actions (Service Bulletin)
Work hours
Parts
Cost per product
Number of U.S.registered airplanes
Fleet cost
Modification (Boeing Service Bulletin
737-78-1082).
Insulation replacement (Boeing Service
Bulletin 737-78-1063).
Software update (CFM CFM56–7B
Service Bulletin 73-0135).
Inspections (Boeing Service Bulletin
737–78–1088).
Modifications (Boeing Service Bulletin
737–78–1069).
Inspections and modification (Boeing
Service Bulletin 737–78–1079) (if
done as an option to Boeing Service
Bulletin 737–78–1088 and Boeing
Service Bulletin 737–78–1082).
14 per engine .......
$2,065 or 3,702 ...
$4,445 or 6,082 ...
710 .......................
Up to $4,318,220.
18 per engine .......
0 ...........................
3,060 ....................
15 .........................
45,900
1 ...........................
0 ...........................
85 .........................
Up to 710 .............
Up to 60,350.
35 .........................
0 ...........................
2,975 ....................
710 .......................
2,112,250
110 .......................
0 ...........................
9,350 ....................
306 .......................
2,861,100
37 per engine .......
2,070 or 3,391 .....
8,360 or 9,681 .....
Optional action .....
Optional action.
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.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
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,
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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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
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:
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
The Boeing Company: Docket No. FAA–
2010–0858; Directorate Identifier 2010–
NM–183–AD.
Comments Due Date
(a) We must receive comments by
November 12, 2010.
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(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 Service Bulletin 737–78–1082, dated
March 25, 2010.
Subject
(d) Air Transport Association (ATA) of
America Code 78: Engine exhaust.
Unsafe Condition
(e) This AD results from reports of heat
damage to the inner wall of the thrust
reversers. The Federal Aviation
Administration is issuing this AD to detect
and correct such heat damage, which could
result in separation of adjacent components
and consequent structural damage to the
airplane, damage to other airplanes, and
injury to people on the ground.
Compliance
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
Affected ADs
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Modification of Thrust Reverser Inner Wall
(g) Except as required by paragraph (m) of
this AD: Within 24 months after the effective
date of this AD, modify the thrust reverser
inner wall, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 737–78–1082, dated March
25, 2010.
Actions Concurrent With Paragraph (g)
(h) Before or concurrently with
accomplishment of the requirements of
paragraph (g) of this AD, do the actions
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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Proposed Rules
specified in paragraphs (h)(1) and (h)(2) of
this AD, as applicable.
(1) For Model 737–600, -700, and -800
series airplanes identified in Boeing Service
Bulletin 737–78–1063, Revision 2, dated
October 7, 1999: Replace the inner wall
blanket insulation, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 737–78–1063, Revision 2,
dated October 7, 1999.
(2) For airplanes equipped with engines
identified in CFM CFM56–7B Service
Bulletin 73–0135, dated March 30, 2007:
Install updated full-authority digital
electronic control (FADEC) software, in
accordance with the Accomplishment
Instructions of CFM CFM56–7B Service
Bulletin 73–0135, dated March 30, 2007.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
Inspection/Measurement
(i) At the applicable time specified in
paragraph (j) of this AD: Do the actions
specified in paragraphs (i)(1), (i)(2), and (i)(3)
of this AD, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 737–78–1088, dated May 12,
2010. If any damage or discrepancy is found,
before further flight, do all applicable
corrective actions, in accordance with
Accomplishment Instructions of Boeing
Service Bulletin 737–78–1088, dated May 12,
2010; except as required by paragraph (k) of
this AD; and except where the service
bulletin refers to ‘‘unsatisfactory’’ findings,
this AD assumes those parts or locations are
‘‘unserviceable.’’
(1) Do a detailed inspection for damage of
the engine side and inner wall side of the
upper and lower insulation blankets.
(2) Measure the electrical conductivity on
the aluminum upper compression pads 2 and
3, as applicable.
(3) Inspect for discrepancies of the thrust
reverser inner wall (including an ultrasonic
inspection for interplay delamination and
skin-to-core disbond, a detailed inspection
for signs of heat damage as applicable, and
a detailed inspection for loose fasteners
where the inner wall attaches to the hinge
beam and at the fasteners for the compression
pads).
Compliance Times for Paragraph (i)
(j) Do the actions specified in paragraph (i)
of this AD at the applicable time specified in
paragraph (j)(1), (j)(2), (j)(3), (j)(4), or (j)(5) of
this AD.
(1) For airplanes with thrust reverser part
number (P/N) 315A2295–003 through
315A2295–154 inclusive: Do the actions
within 30 months after the effective date of
this AD.
(2) For airplanes with thrust reverser P/N
315A2295–155 through 315A2295–174
inclusive: Do the actions within 60 months
after the effective date of this AD.
(3) For airplanes with thrust reverser P/N
315A2295–175 through 315A2295–190
inclusive: Do the actions within 72 months
after the effective date of this AD.
(4) For airplanes with thrust reverser P/N
315A2295–191 through 315A2295–198
inclusive: Do the actions within 84 months
after the effective date of this AD.
(5) For airplanes with thrust reverser P/N
315A2295–199 through 315A2295–202
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inclusive: Do the actions within 96 months
after the effective date of this AD.
Exception to Boeing Service Bulletin 737–78–
1088 Procedures
(k) Where Boeing Service Bulletin 737–78–
1088, dated May 12, 2010, specifies to
contact Boeing for appropriate action, repair
before further flight in accordance with a
method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA. 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.
Actions Concurrent With Paragraph (i)
(l) For airplanes identified in Boeing
Service Bulletin 737–78–1069, Revision 4,
dated June 16, 2005: Before or concurrently
with the accomplishment of the requirements
of paragraph (i) of this AD, modify the thrust
reverser inner wall and insulation blankets,
in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 737–
78–1069, Revision 4, dated June 16, 2005. A
modification done before the effective date of
this AD is also acceptable if done in
accordance with Boeing Service Bulletin
737–78–1069, Revision 1, dated June 13,
2002; Revision 2, dated February 6, 2003; or
Revision 3, dated August 5, 2004.
(m) If the actions required by paragraph (i)
of this AD are done before the compliance
time specified in paragraph (g) of this AD:
Before or concurrently with the
accomplishment of the actions required by
paragraph (i) of this AD, the modification
required by paragraph (g) of this AD must be
done.
Option to Requirements of Paragraphs (g)
and (i)
(n) Accomplishment of all of the actions
(including inspections and modification)
specified in Boeing Service Bulletin 737–78–
1079, Revision 2, dated June 7, 2010, within
24 months after the effective date of this AD,
is acceptable for compliance with the
requirements of paragraphs (g) and (i) of this
AD and is acceptable for compliance with the
requirements of this AD, provided applicable
repairs are done before further flight, and
provided the applicable actions specified in
paragraphs (h)(1), (h)(2), and (l) of this AD
have been done. Actions done before the
effective date of this AD in accordance with
Boeing Service Bulletin 737–78–1079, dated
August 6, 2007; or Revision 1, dated
December 17, 2007; are also acceptable for
compliance with the corresponding actions
specified in this paragraph.
Alternative Methods of Compliance
(AMOCs)
(o)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Chris
Parker, Aerospace Engineer, Propulsion
Branch, ANM–140S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone 425–917–6496; fax 425–917–
6590. Information may be e-mailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
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(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 principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically refer to this AD.
Issued in Renton, Washington on
September 15, 2010.
Robert D. Breneman,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–24175 Filed 9–24–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0942; Directorate
Identifier 2010–CE–049–AD]
RIN 2120–AA64
Airworthiness Directives; British
Aerospace Regional Aircraft Models
Jetstream Series 3101 and Jetstream
Model 3201 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
SUMMARY:
As a result of the fatigue-testing
programme on the Jetstream fatigue test
specimen, it has been identified that failure
of the undercarriage jack mounting shaft
assembly can occur.
This condition, if not corrected, could lead
to a Main Landing Gear (MLG) collapse on
the ground or during landing and
consequently damage to the aeroplane or
injury to the occupants.
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by November 12,
2010.
You may send comments by
any of the following methods:
ADDRESSES:
E:\FR\FM\27SEP1.SGM
27SEP1
]]>Agencies
[Federal Register Volume 75, Number 186 (Monday, September 27, 2010)]
[Proposed Rules]
[Pages 59167-59170]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-24175]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0858; Directorate Identifier 2010-NM-183-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).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Model 737-600, -700, -700C, -800, -900, and -900ER series
airplanes. This proposed AD would require modifying the thrust reverser
inner walls, inspecting for damage of the upper and lower inner wall
insulation blankets, measuring the electrical conductivity on the
aluminum upper compression pads 2 and 3 as applicable, inspecting for
discrepancies of the inner wall of the thrust reverser, and corrective
actions if necessary. This proposed AD would also require, for certain
airplanes, doing various concurrent actions (including replacing the
inner wall blanket insulation, installing updated full-authority
digital electronic control software, and modifying the thrust reverser
inner wall and insulation blankets). This proposed AD results from
reports of heat damage to the inner wall of the thrust reversers. We
are proposing this AD to detect and correct such heat damage, which
could result in separation of adjacent components and consequent
structural damage to the airplane, damage to other airplanes, and
injury to people on the ground.
DATES: We must receive comments on this proposed AD by November 12,
2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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 proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
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 https://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
[[Page 59168]]
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: Chris Parker, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
425-917-6496; 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-2010-0858;
Directorate Identifier 2010-NM-183-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 https://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 reports of heat-related damage to the inner wall
of the thrust reverser. During an inspection of a thrust reverser, one
operator found heat damage at different locations of the inner wall: At
the top, in the area of the number 2 and number 3 upper compression
pads, and at the lower aft edge. A flight test at Boeing showed that
the temperatures applied to the inner walls of the thrust reversers are
too high. Higher temperatures are due to hot precooler air leakage
between the inner wall of the thrust reverser and the insulation
blankets and heat transfer through the upper compression pad area and
the fireseal bracket support flange. Heat damage to the thrust reverser
inner wall, if not corrected, could result in separation of adjacent
components and consequent structural damage to the airplane, damage to
other airplanes, and injury to people on the ground.
Relevant Service Information
We have reviewed the service bulletins identified in the following
table.
Service Information
------------------------------------------------------------------------
Service Bulletin Revision level Date
------------------------------------------------------------------------
Boeing Service Bulletin Original........ March 25, 2010.
737[dash]78[dash]1082.
Boeing Service Bulletin Original........ May 12, 2010.
737[dash]78[dash]1088.
Boeing Service Bulletin 2............... June 7, 2010.
737[dash]78[dash]1079.
Boeing Service Bulletin 4............... June 16, 2005.
737[dash]78[dash]1069.
Boeing Service Bulletin 2............... October 7, 1999.
737[dash]78[dash]1063.
CFM CFM56-7B Service Bulletin Original........ March 30, 2007.
73[dash]0135.
------------------------------------------------------------------------
Boeing Service Bulletin 737-78-1082 describes procedures for
modifying the thrust reverser inner wall by drilling a hole through the
inner wall behind the number 3 upper compression pad, and installing a
bushing, applying sealant to areas of the insulation blankets, and
installing flange insulation assemblies at the top aft edge of the
upper insulation blanket.
Boeing Service Bulletin 737-78-1088 describes procedures for the
following:
Detailed inspection for damage of the engine side and
inner wall side of the upper and lower insulation blankets.
Measurement of the electrical conductivity on the aluminum
upper compression pads 2 and 3, as applicable.
Inspections for discrepancies of the inner wall of the
thrust reverser, including an ultrasonic inspection of the thrust
reverser inner wall for interplay delamination and skin-to-core
disbond.
Detailed inspection, for certain airplanes, of the thrust
reverser inner wall for signs of heat damage.
Detailed inspection of the thrust reverser inner wall for
indications of loose fasteners where the inner wall attaches to the
hinge beam and at the fasteners for the compression pads.
Corrective actions, including repairing or replacing
damaged insulation blankets and repairing the thrust reverser inner
wall (including replacing loose fasteners and contacting Boeing for a
repair procedure), and replacing any unserviceable compression pad with
a new one.
Boeing Service Bulletin 737-78-1079 describes procedures for
essentially the same actions (including inspections and modification)
specified in Boeing Service Bulletins 737-78-1082 and 737-78-1088.
Boeing Service Bulletin 737-78-1082 also specifies the concurrent
accomplishment of the actions specified in Boeing Service Bulletin 737-
78-1063: replacement of the inner wall blanket insulation.
Boeing Service Bulletin 737-78-1082 also specifies the concurrent
accomplishment of the actions specified in CFM CFM56-7B Service
Bulletin 73-0135: installation of updated full-authority digital
electronic control (FADEC) software.
Boeing Service Bulletin 737-78-1088 specifies the concurrent
accomplishment of the actions specified in Boeing Service Bulletin 737-
78-1069: modification of the thrust reverser inner walls and insulation
blankets. The modification involves installing additional supports on
the inner wall of the thrust reverser for the attachment of the
insulation blankets, installing new brackets to attach the forward edge
of the upper and lower insulation blankets, installing additional
attachment grommets to the blankets, and sealing the blankets at the
forward edge of the fan duct inner walls.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs. This proposed AD would require accomplishing the actions
specified in the service information described previously, except as
discussed below.
Differences Between the Proposed AD and Service Information
Although Boeing Service Bulletin 737-78-1088 specifies that
operators may contact the manufacturer for disposition of certain
repair conditions, this proposed AD would require operators to repair
those conditions using a method approved by the FAA.
[[Page 59169]]
Clarification of Certain Terminology
Where Boeing Service Bulletin 737-78-1088 refers to
``unsatisfactory'' findings, this proposed AD assumes those parts or
locations are ``unserviceable.''
Costs of Compliance
We estimate that this proposed AD would affect 710 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD, at an average labor
rate of $85 per hour.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Actions (Service Bulletin) Work hours Parts Cost per product registered airplanes Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification (Boeing Service 14 per engine........ $2,065 or 3,702...... $4,445 or 6,082..... 710................. Up to $4,318,220.
Bulletin 737[dash]78[dash]1082).
Insulation replacement (Boeing 18 per engine........ 0.................... 3,060............... 15.................. 45,900
Service Bulletin
737[dash]78[dash]1063).
Software update (CFM CFM56-7B 1.................... 0.................... 85.................. Up to 710........... Up to 60,350.
Service Bulletin 73[dash]0135).
Inspections (Boeing Service 35................... 0.................... 2,975............... 710................. 2,112,250
Bulletin 737-78-1088).
Modifications (Boeing Service 110.................. 0.................... 9,350............... 306................. 2,861,100
Bulletin 737-78-1069).
Inspections and modification 37 per engine........ 2,070 or 3,391....... 8,360 or 9,681...... Optional action..... Optional action.
(Boeing Service Bulletin 737-78-
1079) (if done as an option to
Boeing Service Bulletin 737-78-
1088 and Boeing Service Bulletin
737-78-1082).
--------------------------------------------------------------------------------------------------------------------------------------------------------
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), 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
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 AD:
The Boeing Company: Docket No. FAA-2010-0858; Directorate Identifier
2010-NM-183-AD.
Comments Due Date
(a) We must receive comments by November 12, 2010.
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 Service Bulletin 737-78-1082,
dated March 25, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 78: Engine
exhaust.
Unsafe Condition
(e) This AD results from reports of heat damage to the inner
wall of the thrust reversers. The Federal Aviation Administration is
issuing this AD to detect and correct such heat damage, which could
result in separation of adjacent components and consequent
structural damage to the airplane, damage to other airplanes, and
injury to people on the ground.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Modification of Thrust Reverser Inner Wall
(g) Except as required by paragraph (m) of this AD: Within 24
months after the effective date of this AD, modify the thrust
reverser inner wall, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 737-78-1082, dated March 25,
2010.
Actions Concurrent With Paragraph (g)
(h) Before or concurrently with accomplishment of the
requirements of paragraph (g) of this AD, do the actions
[[Page 59170]]
specified in paragraphs (h)(1) and (h)(2) of this AD, as applicable.
(1) For Model 737-600, -700, and -800 series airplanes
identified in Boeing Service Bulletin 737-78-1063, Revision 2, dated
October 7, 1999: Replace the inner wall blanket insulation, in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 737-78-1063, Revision 2, dated October 7, 1999.
(2) For airplanes equipped with engines identified in CFM CFM56-
7B Service Bulletin 73-0135, dated March 30, 2007: Install updated
full-authority digital electronic control (FADEC) software, in
accordance with the Accomplishment Instructions of CFM CFM56-7B
Service Bulletin 73-0135, dated March 30, 2007.
Inspection/Measurement
(i) At the applicable time specified in paragraph (j) of this
AD: Do the actions specified in paragraphs (i)(1), (i)(2), and
(i)(3) of this AD, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 737-78-1088, dated May 12,
2010. If any damage or discrepancy is found, before further flight,
do all applicable corrective actions, in accordance with
Accomplishment Instructions of Boeing Service Bulletin 737-78-1088,
dated May 12, 2010; except as required by paragraph (k) of this AD;
and except where the service bulletin refers to ``unsatisfactory''
findings, this AD assumes those parts or locations are
``unserviceable.''
(1) Do a detailed inspection for damage of the engine side and
inner wall side of the upper and lower insulation blankets.
(2) Measure the electrical conductivity on the aluminum upper
compression pads 2 and 3, as applicable.
(3) Inspect for discrepancies of the thrust reverser inner wall
(including an ultrasonic inspection for interplay delamination and
skin-to-core disbond, a detailed inspection for signs of heat damage
as applicable, and a detailed inspection for loose fasteners where
the inner wall attaches to the hinge beam and at the fasteners for
the compression pads).
Compliance Times for Paragraph (i)
(j) Do the actions specified in paragraph (i) of this AD at the
applicable time specified in paragraph (j)(1), (j)(2), (j)(3),
(j)(4), or (j)(5) of this AD.
(1) For airplanes with thrust reverser part number (P/N)
315A2295-003 through 315A2295-154 inclusive: Do the actions within
30 months after the effective date of this AD.
(2) For airplanes with thrust reverser P/N 315A2295-155 through
315A2295-174 inclusive: Do the actions within 60 months after the
effective date of this AD.
(3) For airplanes with thrust reverser P/N 315A2295-175 through
315A2295-190 inclusive: Do the actions within 72 months after the
effective date of this AD.
(4) For airplanes with thrust reverser P/N 315A2295-191 through
315A2295-198 inclusive: Do the actions within 84 months after the
effective date of this AD.
(5) For airplanes with thrust reverser P/N 315A2295-199 through
315A2295-202 inclusive: Do the actions within 96 months after the
effective date of this AD.
Exception to Boeing Service Bulletin 737-78-1088 Procedures
(k) Where Boeing Service Bulletin 737-78-1088, dated May 12,
2010, specifies to contact Boeing for appropriate action, repair
before further flight in accordance with a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA. 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.
Actions Concurrent With Paragraph (i)
(l) For airplanes identified in Boeing Service Bulletin 737-78-
1069, Revision 4, dated June 16, 2005: Before or concurrently with
the accomplishment of the requirements of paragraph (i) of this AD,
modify the thrust reverser inner wall and insulation blankets, in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 737-78-1069, Revision 4, dated June 16, 2005. A
modification done before the effective date of this AD is also
acceptable if done in accordance with Boeing Service Bulletin 737-
78-1069, Revision 1, dated June 13, 2002; Revision 2, dated February
6, 2003; or Revision 3, dated August 5, 2004.
(m) If the actions required by paragraph (i) of this AD are done
before the compliance time specified in paragraph (g) of this AD:
Before or concurrently with the accomplishment of the actions
required by paragraph (i) of this AD, the modification required by
paragraph (g) of this AD must be done.
Option to Requirements of Paragraphs (g) and (i)
(n) Accomplishment of all of the actions (including inspections
and modification) specified in Boeing Service Bulletin 737-78-1079,
Revision 2, dated June 7, 2010, within 24 months after the effective
date of this AD, is acceptable for compliance with the requirements
of paragraphs (g) and (i) of this AD and is acceptable for
compliance with the requirements of this AD, provided applicable
repairs are done before further flight, and provided the applicable
actions specified in paragraphs (h)(1), (h)(2), and (l) of this AD
have been done. Actions done before the effective date of this AD in
accordance with Boeing Service Bulletin 737-78-1079, dated August 6,
2007; or Revision 1, dated December 17, 2007; are also acceptable
for compliance with the corresponding actions specified in this
paragraph.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Chris Parker, Aerospace Engineer, Propulsion Branch, ANM-140S,
FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue,
SW., Renton, Washington 98057-3356; telephone 425-917-6496; fax 425-
917-6590. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically refer to this AD.
Issued in Renton, Washington on September 15, 2010.
Robert D. Breneman,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-24175 Filed 9-24-10; 8:45 am]
BILLING CODE 4910-13-P
