Airworthiness Directives; The Boeing Company Model 737-300, -400, and -500 Series Airplanes, 57882-57885 [2010-23841]
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57882
Federal Register / Vol. 75, No. 184 / Thursday, September 23, 2010 / Proposed Rules
FAA AD Differences
Initial and Repetitive Inspections
(g) Within 2,500 flight cycles after March
2, 2007 (the effective date of AD 2007–02–
22): Do a detailed inspection for any missing,
damaged, or incorrectly installed wiper rings
in the splined couplings of the flap
transmission shafts; and a detailed inspection
for any missing, damaged, or incorrectly
installed rubber gaiters and straps on the
sliding bearing/plunging joints of the flap
transmission; in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–27–2099, dated
February 17, 2006; or Airbus Mandatory
Service Bulletin A310–27–2099, Revision 01,
dated March 21, 2008. Repeat the inspections
thereafter at intervals not to exceed 2,500
flight cycles. After the effective date of this
AD, use only Airbus Mandatory Service
Bulletin A310–27–2099, Revision 01, dated
March 21, 2008.
Note 1: 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.’’
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Corrective Actions
(h) If any damaged, missing or incorrectly
installed wiper rings, rubber gaiters, or straps
are found during any inspection required by
paragraph (g) of this AD: At the applicable
time in paragraph (h)(1) or (h)(2) of this AD,
replace the applicable component with a
serviceable component in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A310–27–2099, dated
February 17, 2006; or Airbus Mandatory
Service Bulletin A310–27–2099, Revision 01,
dated March 21, 2008. After the effective date
of this AD, use only Airbus Mandatory
Service Bulletin A310–27–2099, Revision 01,
dated March 21, 2008.
(1) For airplanes on which the inspection
required by paragraph (g) of this AD has been
done before the effective date of this AD:
Within 400 flight cycles after accomplishing
the inspection.
(2) For airplanes on which the inspection
required by paragraph (g) of this AD has not
been done on or after the effective date of this
AD: Within 400 flight hours after
accomplishing the inspection required by
paragraph (g) of this AD.
DEPARTMENT OF TRANSPORTATION
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
Restatement of Requirements of AD 2007–
02–22, With Revised Service Information
and Reduced Compliance Time for
Corrective Action
Federal Aviation Administration
Other FAA AD Provisions
(j) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, Transport Airplane Directorate, 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:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 227–2125; fax (425)
227–1149. 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 reference this AD. AMOCs
approved previously in accordance with AD
2007–02–22, Amendment 39–14909, are
approved as AMOCs for the corresponding
provisions of paragraphs (g) and (h) of this
AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(k) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2006–
0111R1, dated August 26, 2009; and Airbus
Mandatory Service Bulletin A310–27–2099,
Revision 01, dated March 21, 2008; for
related information.
Issued in Renton, Washington, on
September 10, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
New Requirements of This AD
[FR Doc. 2010–23738 Filed 9–22–10; 8:45 am]
Actions
BILLING CODE 4910–13–P
(i) Accomplishment of the actions required
by paragraph (h) do not terminate the
repetitive inspections required by paragraph
(g) of this AD.
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14:54 Sep 22, 2010
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Frm 00019
Fmt 4702
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14 CFR Part 39
[Docket No. FAA–2010–0855; Directorate
Identifier 2010–NM–066–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–300, –400, and
–500 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Model
737–300, –400, and –500 series
airplanes. The existing AD currently
requires repetitive inspections for
discrepancies of the fuse pins of the
inboard and outboard midspar fittings of
the nacelle strut, and corrective actions
if necessary. This proposed AD would
add replacing the midspar fuse pins
with new, improved fuse pins, which
would terminate the repetitive
inspections. This proposed AD results
from a report of corrosion damage of the
chrome runout on the head side found
on all four midspar fuse pins of the
nacelle strut. Additionally, a large
portion of the chrome plate was missing
from the corroded area of the shank. We
are proposing this AD to prevent
damage of the fuse pins of the inboard
and outboard midspar fittings of the
nacelle strut, which could result in
reduced structural integrity of the fuse
pins, and consequent loss of the strut
and separation of the engine from the
airplane.
SUMMARY:
We must receive comments on
this proposed AD by November 8, 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.
DATES:
E:\FR\FM\23SEP1.SGM
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57883
Federal Register / Vol. 75, No. 184 / Thursday, September 23, 2010 / Proposed Rules
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
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:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6450; 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–2010–0855; Directorate Identifier
2010–NM–066–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
On September 29, 2008, we issued AD
2008–21–03, amendment 39–15687 (73
FR 59493, October 9, 2008), for all
Model 737–300, –400, and –500 series
airplanes. That AD requires repetitive
inspections for discrepancies of the fuse
pins of the inboard and outboard
midspar fittings of the nacelle strut, and
corrective actions if necessary. That AD
resulted from a report of corrosion
damage of the chrome runout on the
head side found on all four midspar fuse
pins of the nacelle strut. Additionally, a
large portion of the chrome plate was
missing from the corroded area of the
shank. We issued that AD to detect and
correct discrepancies of the fuse pins of
the inboard and outboard midspar
fittings of the nacelle strut, which could
result in reduced structural integrity of
the fuse pins, and consequent loss of the
strut and separation of the engine from
the airplane.
Actions Since Existing AD Was Issued
In the preamble to the NPRM of AD
2008–21–03, the FAA specified that the
actions required by that AD were
considered ‘‘interim action’’ and that the
manufacturer was developing a
modification to address the unsafe
condition. The FAA indicated that it
may consider further rulemaking action
once the modification was developed,
approved, and available. The
manufacturer now has developed such a
modification, and the FAA has
determined that further rulemaking
action is indeed necessary; this
proposed AD follows from that
determination.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 737–54A1044, Revision
2, dated January 20, 2010. The repetitive
detailed inspections and corrective
actions are similar to those described in
Boeing Special Attention Service
Bulletin 737–54–1044, dated December
10, 2007 (referenced in AD 2008–21–03
as the appropriate source of service
information). Revision 2 of the service
bulletin adds procedures for replacing
the midspar fuse pins with new,
improved fuse pins. Replacement with
the new, improved fuse pin eliminates
the need for repetitive detailed
inspections.
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 2008–
21–03 and would retain the
requirements of the existing AD. This
proposed AD would also require
replacing the midspar fuse pins with
new, improved fuse pins, which would
terminate the requirement for repetitive
detailed inspections.
Change to Existing AD
This proposed AD would retain all
requirements of AD 2008–21–03. Since
AD 2008–21–03 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, paragraph (f) of the existing AD
has been re-identified as paragraph (g)
in this NPRM.
Costs of Compliance
There are about 1,961 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Average labor
rate per hour
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Action
Work hours
Repetitive detailed inspections (required
by AD 2008–21–03).
Midspar fuse pin replacement (new proposed action).
4 .................................
$85
1 per pin (up to 4 pins
per airplane).
85
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14:54 Sep 22, 2010
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Frm 00020
Cost per
airplane
Parts
Number of
U.S.registered
airplanes
Fleet cost
None ........
$340, per inspection
cycle.
616
$209,440, per inspection cycle.
$843 per
pin.
Up to $3,712 ..............
616
Up to $2,286,592.
Fmt 4702
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57884
Federal Register / Vol. 75, No. 184 / Thursday, September 23, 2010 / Proposed Rules
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
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, 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:
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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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–15687 (73 FR
59493, October 9, 2008) and adding the
following new AD:
The Boeing Company: Docket No. FAA–
2010–0855; Directorate Identifier 2010–
NM–066–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by November 8, 2010.
Affected ADs
(b) This AD supersedes AD 2008–21–03,
Amendment 39–15687.
Applicability
(c) This AD applies to all The Boeing
Company Model 737–300, –400, and –500
series airplanes, certificated in any category.
Subject
(d) Air Transport Association (ATA) of
America Code 54: Nacelles/Pylons.
Unsafe Condition
(e) This AD results from a report of
corrosion damage of the chrome runout on
the head side found on all four midspar fuse
pins of the nacelle strut. Additionally, a large
portion of the chrome plate was missing from
the corroded area of the shank. The Federal
Aviation Administration is issuing this AD to
prevent damage of the fuse pins of the
inboard and outboard midspar fittings of the
nacelle strut, which could result in reduced
structural integrity of the fuse pins, and
consequent loss of the strut and separation of
the engine from the airplane.
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.
Restatement of Requirements of AD 2008–
21–03
Repetitive Inspections/Corrective Actions,
With Revised Service Information
(g) At the applicable time specified in
paragraph 1.E., ‘‘Compliance’’ of Boeing
Special Attention Service Bulletin 737–54–
1044, dated December 10, 2007; except,
where the service bulletin specifies a
compliance time after the date on the service
bulletin, this AD requires compliance within
the specified compliance time after
November 13, 2008 (the effective date of AD
2008–21–03): Do a detailed inspection for
discrepancies of the fuse pins of the inboard
and outboard midspar fittings of the nacelle
strut by doing all the actions, including all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
737–54–1044, dated December 10, 2007; or
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Frm 00021
Fmt 4702
Sfmt 4702
Boeing Alert Service Bulletin 737–54A1044,
Revision 2, dated January 20, 2010. Do all
applicable corrective actions before further
flight. Repeat the inspection at the time
specified in paragraph 1.E. of Boeing Special
Attention Service Bulletin 737–54–1044,
dated December 10, 2007. Accomplishing the
actions of paragraph (h) of this AD terminates
the requirements of this paragraph.
New Requirements of This AD
Replacement
(h) Within 120 months after the effective
date of this AD, replace all midspar fuse pins
having part number (P/N) 311A1092–2 with
a midspar fuse pin having P/N 311A1092–3,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–54A1044, Revision 2, dated January 20,
2010. Accomplishing the requirements of this
paragraph terminates the requirements of
paragraph (g) of this AD for that fuse pin.
Actions Accomplished According to
Previous Revision of Service Information
(i) Actions done before the effective date of
this AD in accordance with Boeing Special
Attention Service Bulletin 737–54–1044,
Revision 1, dated November 26, 2008, are
acceptable for compliance with the
corresponding requirements of this AD.
Alternative Methods of Compliance
(AMOCs)
(j)(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: Alan
Pohl, Aerospace Engineer, Airframe Branch,
ANM–120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6450; fax (425) 917–6590.
Information may be e-mailed to: 9-ANMSeattle-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 reference this AD.
(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 the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that 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.
(4) AMOCs approved in accordance with
the requirements of AD 2008–21–03 are
acceptable for the corresponding
requirements of this AD.
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Federal Register / Vol. 75, No. 184 / Thursday, September 23, 2010 / Proposed Rules
Issued in Renton, Washington, on
September 15, 2010.
Robert D. Breneman,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–23841 Filed 9–22–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0856; Directorate
Identifier 2010–NM–117–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–600, –700, –700C,
–800, and –900 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, and
–900 series airplanes. This proposed AD
would require inspecting for part
numbers of the operational program
software of the flight control computers,
and doing corrective actions if
necessary. This proposed AD results
from reports of erroneous undetected
output from a single radio altimeter
channel, which resulted in premature
autothrottle retard during approach. We
are proposing this AD to detect and
correct erroneous output from a radio
altimeter channel, which could result in
premature autothrottle landing flare
retard and the loss of automatic speed
control, and consequent loss of control
of the airplane.
DATES: We must receive comments on
this proposed AD by November 8, 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
wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
SUMMARY:
VerDate Mar<15>2010
14:54 Sep 22, 2010
Jkt 220001
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
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:
Richard Reed, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office (ACO), 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356;
telephone (425) 917–6431; 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–2010–0856; Directorate Identifier
2010–NM–117–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 a number
of instances in service, of erroneous
undetected output from a single radio
altimeter channel, which resulted in
PO 00000
Frm 00022
Fmt 4702
Sfmt 4702
57885
premature autothrottle retard during
approach. This condition can lead to
premature autothrottle landing flare
retard and the loss of automatic speed
control, and consequent loss of control
of the airplane.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 737–22A1211, dated
April 13, 2010, which describes
procedures for inspecting to determine
the operational program software part
numbers of the flight control computers,
and installing new software if necessary.
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.
Costs of Compliance
We estimate that this proposed AD
would affect 207 airplanes of U.S.
registry. We also estimate that it would
take about 1 work-hour per product to
comply with the inspection of this
proposed AD. The average labor rate is
$85 per work-hour. Based on these
figures, we estimate the cost of the
inspection of this proposed AD to the
U.S. operators to be $17,595, or $85 per
product.
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
E:\FR\FM\23SEP1.SGM
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]]>Agencies
[Federal Register Volume 75, Number 184 (Thursday, September 23, 2010)]
[Proposed Rules]
[Pages 57882-57885]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-23841]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0855; Directorate Identifier 2010-NM-066-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 737-300, -400,
and -500 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 Model 737-300, -400, and -500 series
airplanes. The existing AD currently requires repetitive inspections
for discrepancies of the fuse pins of the inboard and outboard midspar
fittings of the nacelle strut, and corrective actions if necessary.
This proposed AD would add replacing the midspar fuse pins with new,
improved fuse pins, which would terminate the repetitive inspections.
This proposed AD results from a report of corrosion damage of the
chrome runout on the head side found on all four midspar fuse pins of
the nacelle strut. Additionally, a large portion of the chrome plate
was missing from the corroded area of the shank. We are proposing this
AD to prevent damage of the fuse pins of the inboard and outboard
midspar fittings of the nacelle strut, which could result in reduced
structural integrity of the fuse pins, and consequent loss of the strut
and separation of the engine from the airplane.
DATES: We must receive comments on this proposed AD by November 8,
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.
[[Page 57883]]
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 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: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6450; 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-2010-0855;
Directorate Identifier 2010-NM-066-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
On September 29, 2008, we issued AD 2008-21-03, amendment 39-15687
(73 FR 59493, October 9, 2008), for all Model 737-300, -400, and -500
series airplanes. That AD requires repetitive inspections for
discrepancies of the fuse pins of the inboard and outboard midspar
fittings of the nacelle strut, and corrective actions if necessary.
That AD resulted from a report of corrosion damage of the chrome runout
on the head side found on all four midspar fuse pins of the nacelle
strut. Additionally, a large portion of the chrome plate was missing
from the corroded area of the shank. We issued that AD to detect and
correct discrepancies of the fuse pins of the inboard and outboard
midspar fittings of the nacelle strut, which could result in reduced
structural integrity of the fuse pins, and consequent loss of the strut
and separation of the engine from the airplane.
Actions Since Existing AD Was Issued
In the preamble to the NPRM of AD 2008-21-03, the FAA specified
that the actions required by that AD were considered ``interim action''
and that the manufacturer was developing a modification to address the
unsafe condition. The FAA indicated that it may consider further
rulemaking action once the modification was developed, approved, and
available. The manufacturer now has developed such a modification, and
the FAA has determined that further rulemaking action is indeed
necessary; this proposed AD follows from that determination.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 737-54A1044,
Revision 2, dated January 20, 2010. The repetitive detailed inspections
and corrective actions are similar to those described in Boeing Special
Attention Service Bulletin 737-54-1044, dated December 10, 2007
(referenced in AD 2008-21-03 as the appropriate source of service
information). Revision 2 of the service bulletin adds procedures for
replacing the midspar fuse pins with new, improved fuse pins.
Replacement with the new, improved fuse pin eliminates the need for
repetitive detailed inspections.
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 2008-21-03 and would retain the requirements of the
existing AD. This proposed AD would also require replacing the midspar
fuse pins with new, improved fuse pins, which would terminate the
requirement for repetitive detailed inspections.
Change to Existing AD
This proposed AD would retain all requirements of AD 2008-21-03.
Since AD 2008-21-03 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, paragraph (f) of
the existing AD has been re-identified as paragraph (g) in this NPRM.
Costs of Compliance
There are about 1,961 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
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Number of
Average labor U.S.-
Action Work hours rate per hour Parts Cost per airplane registered Fleet cost
airplanes
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Repetitive detailed inspections 4.................... $85 None................ $340, per inspection 616 $209,440, per
(required by AD 2008-21-03). cycle. inspection cycle.
Midspar fuse pin replacement (new 1 per pin (up to 4 85 $843 per pin........ Up to $3,712........ 616 Up to $2,286,592.
proposed action). pins per airplane).
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[[Page 57884]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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 removing amendment 39-15687 (73 FR
59493, October 9, 2008) and adding the following new AD:
The Boeing Company: Docket No. FAA-2010-0855; Directorate Identifier
2010-NM-066-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by November
8, 2010.
Affected ADs
(b) This AD supersedes AD 2008-21-03, Amendment 39-15687.
Applicability
(c) This AD applies to all The Boeing Company Model 737-300, -
400, and -500 series airplanes, certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 54:
Nacelles/Pylons.
Unsafe Condition
(e) This AD results from a report of corrosion damage of the
chrome runout on the head side found on all four midspar fuse pins
of the nacelle strut. Additionally, a large portion of the chrome
plate was missing from the corroded area of the shank. The Federal
Aviation Administration is issuing this AD to prevent damage of the
fuse pins of the inboard and outboard midspar fittings of the
nacelle strut, which could result in reduced structural integrity of
the fuse pins, and consequent loss of the strut and separation of
the engine from the airplane.
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.
Restatement of Requirements of AD 2008-21-03
Repetitive Inspections/Corrective Actions, With Revised Service
Information
(g) At the applicable time specified in paragraph 1.E.,
``Compliance'' of Boeing Special Attention Service Bulletin 737-54-
1044, dated December 10, 2007; except, where the service bulletin
specifies a compliance time after the date on the service bulletin,
this AD requires compliance within the specified compliance time
after November 13, 2008 (the effective date of AD 2008-21-03): Do a
detailed inspection for discrepancies of the fuse pins of the
inboard and outboard midspar fittings of the nacelle strut by doing
all the actions, including all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-54-1044, dated December 10, 2007; or
Boeing Alert Service Bulletin 737-54A1044, Revision 2, dated January
20, 2010. Do all applicable corrective actions before further
flight. Repeat the inspection at the time specified in paragraph
1.E. of Boeing Special Attention Service Bulletin 737-54-1044, dated
December 10, 2007. Accomplishing the actions of paragraph (h) of
this AD terminates the requirements of this paragraph.
New Requirements of This AD
Replacement
(h) Within 120 months after the effective date of this AD,
replace all midspar fuse pins having part number (P/N) 311A1092-2
with a midspar fuse pin having P/N 311A1092-3, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-54A1044, Revision 2, dated January 20, 2010. Accomplishing the
requirements of this paragraph terminates the requirements of
paragraph (g) of this AD for that fuse pin.
Actions Accomplished According to Previous Revision of Service
Information
(i) Actions done before the effective date of this AD in
accordance with Boeing Special Attention Service Bulletin 737-54-
1044, Revision 1, dated November 26, 2008, are acceptable for
compliance with the corresponding requirements of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(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: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA,
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 917-6450; 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 reference this AD.
(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 the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that 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.
(4) AMOCs approved in accordance with the requirements of AD
2008-21-03 are acceptable for the corresponding requirements of this
AD.
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Issued in Renton, Washington, on September 15, 2010.
Robert D. Breneman,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-23841 Filed 9-22-10; 8:45 am]
BILLING CODE 4910-13-P
