Airworthiness Directives; The Boeing Company Model 747-400 and 747-400D Series Airplanes, 27966-27969 [2010-11901]
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27966
Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Rolls-Royce plc: Docket No. FAA–2009–
1157; Directorate Identifier 2009–NE–
26–AD.
Comments Due Date
(a) We must receive comments by July 6,
2010.
Affected Airworthiness Directives (ADs)
(b) None.
Applicability
(c) This AD applies to Rolls-Royce plc
RB211–22B series and RB211–524B4–D–02,
RB211–524D4–19, RB211–524D4–39,
RB211–524D4–B–19, RB211–524D4–B–39,
RB211–524D4X–19, and RB211–524D4X–B–
19 model turbofan engines. These engines are
installed on, but not limited to, Boeing 747
series and Lockheed L–1011 series airplanes.
Reason
(d) This AD results from:
Several low pressure turbine (LPT) shafts
have been found with cracks originating from
the rear cooling air holes. The cracks were
found at normal component overhaul, by the
standard Magnetic Particle Inspection (MPI)
technique defined in the associated engine
manual. The cracks have been found to
initiate from corrosion pits. Propagation of a
crack from the rear cooling air holes may
result in shaft failure and subsequently in an
uncontained Low Pressure Turbine failure.
For the reasons stated above, this AD requires
the inspection of the affected engines’ LPT
shafts and replacement of the shaft, as
necessary.
We are issuing this AD to detect cracks,
initiated by corrosion pits, originating from
the rear cooling air holes, which could result
in shaft failure and subsequently in an
uncontained failure of the LPT and damage
to the airplane.
Actions and Compliance
(e) Unless already done, do the following
actions.
Initial Inspection Requirements
(1) At the next engine shop visit after the
effective date of this AD when the LPT shaft
is completely disassembled to piece-part
level, inspect the LPT shaft using paragraphs
3.A.(1)(a) through 3.A.(4)(l) of the
accomplishment instructions of Rolls-Royce
Service Bulletin RB.211–72–AF336, dated
October 24, 2007.
Repetitive Inspection Requirements
(2) Thereafter, reinspect the LPT shaft
using paragraphs 3.A.(1)(a) through 3.A.(4)(l)
of the accomplishment instructions of RollsRoyce Service Bulletin RB.211–72–AF336,
dated October 24, 2007 and the following
schedule in Table 1 of this AD:
TABLE 1—REPETITIVE INSPECTION INTERVAL BY ENGINE MODEL
Engine model
Maximum time between inspections (engine cycles)
(i) RB211–22B Series, all models ............................................................
(ii) RB211–524B4–D–02 ...........................................................................
(iii) RB211–524D4–19, RB211–524D4–39, RB211–524D4–B–19,
RB211–524D4–B–39, RB211–524D4X–19 and RB211–524D4X–B–
19.
Remove Parts With Cracks
(3) Remove cracked LPT shafts, found
using paragraphs (e)(1) or (e)(2) of this AD,
from service before further flight.
Definitions
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(4) For the purpose of this AD, an engine
shop visit is the induction of an engine into
the shop for maintenance involving the
separation of pairs of major mating engine
flanges. The separation of engine flanges
solely for the purposes of transportation
without subsequent engine maintenance does
not constitute an engine shop visit.
Other FAA AD Provisions
(f) Alternative Methods of Compliance
(AMOCs): The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(g) Refer to MCAI EASA Airworthiness
Directive 2007–0310 R1, dated January 8,
VerDate Mar<15>2010
13:46 May 18, 2010
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3,500.
4,000.
At the next engine shop visit after the last inspection.
2008, and Rolls-Royce plc Alert Service
Bulletin RB.211–72–AF336, dated October
24, 2007, for related information. Contact
Rolls-Royce plc P.O. Box 31, Derby, DE24
8BJ, United Kingdom; telephone 044 1332
242424; fax 044 1332 249936, for a copy of
this service information.
(h) Contact Tara Chaidez, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: tara.chaidez@faa.gov;
telephone (781) 238–7773; fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
May 12, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2010–11998 Filed 5–18–10; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0480; Directorate
Identifier 2010–NM–035–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747–400 and 747–
400D Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Model 747–400 and 747–400D series
airplanes. This proposed AD would
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Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules
require installing aluminum gutter
reinforcing brackets to the forward and
aft drip shield gutters of the main
equipment center (MEC); and adding a
reinforcing fiberglass overcoat to the top
surface of the MEC drip shield,
including an inspection for cracking and
holes in the MEC drip shield, and
corrective actions if necessary. This
proposed AD also provides for an option
to install an MEC drip shield drain
system, which, if accomplished, would
extend the compliance time for adding
the reinforcing fiberglass overcoat to the
top surface of the MEC drip shield. This
proposed AD results from a report
indicating that an operator experienced
a multi-power system loss in-flight of
#1, #2, and #3 alternating current (AC)
electrical power systems located in the
MEC. We are proposing this AD to
prevent water penetration into the MEC,
which could result in the loss of flight
critical systems.
DATES: We must receive comments on
this proposed AD by July 6, 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
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:
Marcia Smith, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6484; 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–2010–0480; Directorate Identifier
2010–NM–035–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 received a report indicating that
an operator experienced a multi-power
system loss in-flight of #1, #2, and #3
AC electrical power systems located in
the main equipment center (MEC). The
forward MEC drip shield gutters and
exhaust plenum have each been
identified as part of the leak path into
the MEC. Multiple operators have
reported MEC drip shield gutter and
upper surface cracks. These cracks can
allow water to penetrate the MEC drip
shield and enter the MEC. This
condition, if not corrected, could allow
water penetration into the MEC, which
could result in the loss of flight critical
systems.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 747–25A3555, dated
November 4, 2009. The service bulletin
describes procedures for installing
aluminum gutter reinforcing brackets to
the forward and aft drip shield gutters
of the main equipment center (MEC).
The service bulletin also describes
procedures for adding a reinforcing
fiberglass overcoat to the top surface of
the MEC drip shield, including a general
visual inspection for cracking and holes
in the top surface of the MEC drip
shield, and corrective actions if
necessary. The corrective actions
include repairing any crack or hole
found. The service bulletin also
describes procedures for an option to
install an MEC drip shield drain system,
which, if accomplished, would extend
the compliance time for adding the
reinforcing fiberglass overcoat.
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 the same
type design. 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 71 airplanes of U.S.
registry. The following table provides
the estimated costs, depending on
airplane configuration, for U.S.
operators to comply with this proposed
AD.
erowe on DSK5CLS3C1PROD with PROPOSALS-1
TABLE—ESTIMATED COSTS
Average
labor rate
per hour
Action
Work hours
Install Brackets ..........
Add Overcoat ............
Between 7 and 8 1 ..
Between 11 and 12 1
VerDate Mar<15>2010
13:46 May 18, 2010
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$85
85
Number of
U.S.registered
airplanes
Parts
Cost per product
None ........................
None ........................
Up to $680 1 ............
Up to $1,020 1 .........
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71
71
Fleet cost
Up to $48,280.1
Up to $72,420.1
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Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules
TABLE—ESTIMATED COSTS—Continued
Average
labor rate
per hour
Action
Work hours
Install Optional MEC
Drip Shield Drain
System.
Between 12 and 13 1
1 Depending
85
Cost per product
Up to $8,982 1 .........
Up to $10,087 1 .......
The Proposed Amendment
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
Regulatory Findings
erowe on DSK5CLS3C1PROD with PROPOSALS-1
71
Fleet cost
Up to $716,177.1
on work package.
Authority for This Rulemaking
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.
VerDate Mar<15>2010
Number of
U.S.registered
airplanes
Parts
13:46 May 18, 2010
Jkt 220001
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 adding
the following new AD:
The Boeing Company: Docket No. FAA–
2010–0480; Directorate Identifier 2010–
NM–035–AD.
Comments Due Date
(a) We must receive comments by July 6,
2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing
Company Model 747–400 and 747–400D
series airplanes, certificated in any category;
as identified in Boeing Alert Service Bulletin
747–25A3555, dated November 4, 2009.
Subject
(d) Air Transport Association (ATA) of
America Code 25: Equipment/Furnishings.
Unsafe Condition
(e) This AD results from a report indicating
that an operator experienced a multi-power
system loss in-flight of #1, #2, and #3
alternating current electrical power systems
located in the main equipment center (MEC).
The Federal Aviation Administration is
issuing this AD to prevent water penetration
into the MEC, which could result in loss of
flight critical systems.
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
(g) Do the actions specified in either
paragraph (g)(1) or (g)(2) of this AD, at the
times specified in those paragraphs, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
PO 00000
Frm 00020
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747–25A3555, dated November 4, 2009 (‘‘the
service bulletin’’).
(1) Within 24 months after the effective
date of this AD, install the reinforcing
brackets of the MEC drip shield aluminum
gutter, in accordance with Work Package 1 of
the Accomplishment Instructions of the
service bulletin; and add a reinforcing
fiberglass overcoat to the top surface of the
MEC drip shield, including doing a general
visual inspection for cracking and holes in
the top surface of the MEC drip shield, and
doing all applicable corrective actions, in
accordance with Work Package 3 of the
Accomplishment Instructions of the service
bulletin. Do all applicable corrective actions
before further flight after doing the general
visual inspection.
(2) Do the actions specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within 24 months after the effective
date of this AD, install the reinforcing
brackets of the MEC drip shield aluminum
gutter, in accordance with Work Package 1 of
the Accomplishment Instructions of the
service bulletin; and install a MEC drip
shield drain system, in accordance with
Work Package 2 of the Accomplishment
Instructions of the service bulletin.
(ii) Within 96 months after the effective
date of this AD, add a reinforcing fiberglass
overcoat to the top surface of the MEC drip
shield, including doing a general visual
inspection for cracking and holes in the top
surface of the MEC drip shield, and doing all
applicable corrective actions, in accordance
with Work Package 3 of the Accomplishment
Instructions of the service bulletin. Do all
applicable corrective actions before further
flight after doing the general visual
inspection.
Alternative Methods of Compliance
(AMOCs)
(h)(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:
Marcia Smith, Aerospace Engineer, Cabin
Safety and Environmental Systems Branch,
ANM–150S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6484; 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
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Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules
(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.
Issued in Renton, Washington, on May 5,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–11901 Filed 5–18–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0481; Directorate
Identifier 2009–NM–192–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–100 and –200
Series Airplanes
erowe on DSK5CLS3C1PROD with PROPOSALS-1
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Model 737–100 and –200 series
airplanes. This proposed AD would
require repetitive inspections for
cracking and damaged fasteners of
certain fuselage frames and stub beams,
and corrective actions if necessary. For
certain airplanes, this proposed AD
would also require repetitive
inspections for cracking of the inboard
chord fastener hole of the frame at body
station 639, stringer S–16, and
corrective actions if necessary. For
certain airplanes, this proposed AD
would also require an inspection to
determine the edge margin of the lower
chord. For airplanes with a certain short
edge margin, this proposed AD requires
repetitive inspections for cracking, and
corrective actions if necessary; replacing
the lower chord terminates the
repetitive inspections. This proposed
AD requires an eventual preventive
modification. For certain airplanes,
doing the modification or a repair
would terminate the repetitive
inspections for the repaired or modified
frame only. For airplanes on which the
modification or repair is done at certain
body stations, this proposed AD would
require repetitive inspections for
cracking of certain frame webs and
inner and outer chords, and corrective
actions if necessary. For certain other
airplanes, this proposed AD requires a
modification which includes reinforcing
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13:46 May 18, 2010
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the body frame inner chords, replacing
the stub beam upper chords and attach
angles, and reinforcing the stub beam
web. This proposed AD results from
reports of fatigue cracks at certain frame
sections, in addition to stub beam
cracking, caused by high flight cycle
stresses from both pressurization and
maneuver load. We are proposing this
AD to detect and correct fatigue
cracking of certain fuselage frames and
stub beams, and possible severed
frames, which could result in reduced
structural integrity of the frames. This
reduced structural integrity can increase
loading in the fuselage skin, which will
accelerate skin crack growth and result
in rapid decompression of the fuselage.
DATES: We must receive comments on
this proposed AD by July 6, 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
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
PO 00000
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27969
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6447; 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–2010–0481; Directorate Identifier
2009–NM–192–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 fatigue
cracks found at certain frame sections,
in addition to stub beam cracking,
caused by high flight cycle stresses from
both pressurization and maneuver load.
Numerous cracks were found in the
shear ties, webs, and inboard and
outboard chords of the overwing body
frames and stub beams between body
stations 559 and 639. Cracks were also
found in the webs, attach angles, and
the upper and lower chords of the stub
beams. There were reports of sheared
fasteners in the overwing body frames
and stub beams in the same location.
Fatigue cracking of certain fuselage
frames and stub beams, if not detected
and corrected, and possible severed
frames, could result in reduced
structural integrity of the frames. This
reduced structural integrity can increase
loading in the fuselage skin, which will
accelerate skin crack growth and result
in rapid decompression of the fuselage.
Relevant Service Information
We have reviewed Boeing Service
Bulletin 737–53–1061, Revision 4,
including Addendum, dated July 16,
1992. For airplanes on which a repair
(Part III) or preventive modification
(Part II) has not been done, the service
bulletin describes procedures for
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]]>Agencies
[Federal Register Volume 75, Number 96 (Wednesday, May 19, 2010)]
[Proposed Rules]
[Pages 27966-27969]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-11901]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0480; Directorate Identifier 2010-NM-035-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747-400 and
747-400D Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Model 747-400 and 747-400D series airplanes. This proposed AD
would
[[Page 27967]]
require installing aluminum gutter reinforcing brackets to the forward
and aft drip shield gutters of the main equipment center (MEC); and
adding a reinforcing fiberglass overcoat to the top surface of the MEC
drip shield, including an inspection for cracking and holes in the MEC
drip shield, and corrective actions if necessary. This proposed AD also
provides for an option to install an MEC drip shield drain system,
which, if accomplished, would extend the compliance time for adding the
reinforcing fiberglass overcoat to the top surface of the MEC drip
shield. This proposed AD results from a report indicating that an
operator experienced a multi-power system loss in-flight of 1,
2, and 3 alternating current (AC) electrical power
systems located in the MEC. We are proposing this AD to prevent water
penetration into the MEC, which could result in the loss of flight
critical systems.
DATES: We must receive comments on this proposed AD by July 6, 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 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: Marcia Smith, Aerospace Engineer,
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6484; 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-2010-0480;
Directorate Identifier 2010-NM-035-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 received a report indicating that an operator experienced a
multi-power system loss in-flight of 1, 2, and
3 AC electrical power systems located in the main equipment
center (MEC). The forward MEC drip shield gutters and exhaust plenum
have each been identified as part of the leak path into the MEC.
Multiple operators have reported MEC drip shield gutter and upper
surface cracks. These cracks can allow water to penetrate the MEC drip
shield and enter the MEC. This condition, if not corrected, could allow
water penetration into the MEC, which could result in the loss of
flight critical systems.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-25A3555, dated
November 4, 2009. The service bulletin describes procedures for
installing aluminum gutter reinforcing brackets to the forward and aft
drip shield gutters of the main equipment center (MEC). The service
bulletin also describes procedures for adding a reinforcing fiberglass
overcoat to the top surface of the MEC drip shield, including a general
visual inspection for cracking and holes in the top surface of the MEC
drip shield, and corrective actions if necessary. The corrective
actions include repairing any crack or hole found. The service bulletin
also describes procedures for an option to install an MEC drip shield
drain system, which, if accomplished, would extend the compliance time
for adding the reinforcing fiberglass overcoat.
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 the same type design.
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 71 airplanes of U.S.
registry. The following table provides the estimated costs, depending
on airplane configuration, for U.S. operators to comply with this
proposed AD.
Table--Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average U.S.-
Action Work hours labor rate Parts Cost per product registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Install Brackets.................. Between 7 and 8 \1\.. $85 None................. Up to $680 \1\....... 71 Up to $48,280.\1\
Add Overcoat...................... Between 11 and 12 \1\ 85 None................. Up to $1,020 \1\..... 71 Up to $72,420.\1\
[[Page 27968]]
Install Optional MEC Drip Shield Between 12 and 13 \1\ 85 Up to $8,982 \1\..... Up to $10,087 \1\.... 71 Up to $716,177.\1\
Drain System.
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ Depending on work package.
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-2010-0480; Directorate Identifier
2010-NM-035-AD.
Comments Due Date
(a) We must receive comments by July 6, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 747-400 and 747-
400D series airplanes, certificated in any category; as identified
in Boeing Alert Service Bulletin 747-25A3555, dated November 4,
2009.
Subject
(d) Air Transport Association (ATA) of America Code 25:
Equipment/Furnishings.
Unsafe Condition
(e) This AD results from a report indicating that an operator
experienced a multi-power system loss in-flight of 1,
2, and 3 alternating current electrical power
systems located in the main equipment center (MEC). The Federal
Aviation Administration is issuing this AD to prevent water
penetration into the MEC, which could result in loss of flight
critical systems.
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
(g) Do the actions specified in either paragraph (g)(1) or
(g)(2) of this AD, at the times specified in those paragraphs, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-25A3555, dated November 4, 2009 (``the service
bulletin'').
(1) Within 24 months after the effective date of this AD,
install the reinforcing brackets of the MEC drip shield aluminum
gutter, in accordance with Work Package 1 of the Accomplishment
Instructions of the service bulletin; and add a reinforcing
fiberglass overcoat to the top surface of the MEC drip shield,
including doing a general visual inspection for cracking and holes
in the top surface of the MEC drip shield, and doing all applicable
corrective actions, in accordance with Work Package 3 of the
Accomplishment Instructions of the service bulletin. Do all
applicable corrective actions before further flight after doing the
general visual inspection.
(2) Do the actions specified in paragraphs (g)(2)(i) and
(g)(2)(ii) of this AD.
(i) Within 24 months after the effective date of this AD,
install the reinforcing brackets of the MEC drip shield aluminum
gutter, in accordance with Work Package 1 of the Accomplishment
Instructions of the service bulletin; and install a MEC drip shield
drain system, in accordance with Work Package 2 of the
Accomplishment Instructions of the service bulletin.
(ii) Within 96 months after the effective date of this AD, add a
reinforcing fiberglass overcoat to the top surface of the MEC drip
shield, including doing a general visual inspection for cracking and
holes in the top surface of the MEC drip shield, and doing all
applicable corrective actions, in accordance with Work Package 3 of
the Accomplishment Instructions of the service bulletin. Do all
applicable corrective actions before further flight after doing the
general visual inspection.
Alternative Methods of Compliance (AMOCs)
(h)(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: Marcia Smith, Aerospace Engineer, Cabin Safety and
Environmental Systems Branch, ANM-150S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 917-6484; 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
[[Page 27969]]
(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.
Issued in Renton, Washington, on May 5, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-11901 Filed 5-18-10; 8:45 am]
BILLING CODE 4910-13-P
