Airworthiness Directives; Eurocopter France Model AS355E, F, F1, F2, and N Helicopters, 38529-38532 [E7-13624]
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jlentini on PROD1PC65 with PROPOSALS
Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules
(c) For Type 1 and Type 3 vertical fins,
inspect the vertical fin and fin support
bracket for paint, and the vertical fin
attaching hardware for proper torque, in
accordance with steps 5. and 6. of the
Accomplishment Instructions of the ASB.
(d) For Type 2 vertical fins, inspect the
vertical fin and fin support bracket for paint,
the vertical fin attaching hardware for proper
torque, and the amount of gap between the
vertical fin support bracket and the vertical
fin doubler in accordance with steps 5., 6.,
and 7. of the Accomplishment Instructions of
the ASB.
(e) If the inspections required by
paragraphs (c) and (d) of this AD indicate
that the torque and gap are within limits, and
there is no paint present, visually inspect the
vertical fin support bracket in the area of the
vertical fin attaching hardware for a crack
using a 10x or higher power magnifying
glass.
(1) If no crack is found, re-torque the
vertical fin attaching hardware to between 75
and 95 in. lbs. (8.47 to 10.75 Nm).
(2) If a crack is found, replace the twopiece vertical fin support bracket with a onepiece vertical fin casting support, P/N 206–
033–426–003.
(f) Based on your finding in paragraphs (c)
and (d) of this AD, if either the torque or gap
is out of limits, or paint is present:
(1) Remove the vertical fin.
(2) Remove all the primer and paint
coatings in the areas indicated in Figure I of
the ASB.
(3) Fluorescent penetrant inspect (FPI) the
vertical fin support.
(4) If a crack is found, replace the twopiece vertical fin support with a one-piece
vertical fin casting support, P/N 206–033–
426–003.
(5) If no crack is found, apply two coats of
Polyamide Epoxy Primer on bare metal
surfaces.
(g) For Type 2 vertical fins only:
(1) If incorrect washers (spacers) or no
washers are installed, visually inspect the 4
vertical fin potted inserts as depicted in the
vertical fin detail in Figure I of the ASB for
any damage using a 10x or higher power
magnifying glass.
(2) If any of the 4 vertical fin potted inserts
is damaged with no other damage to the
surrounding areas, remove and replace the
damaged potted insert with an airworthy
potted insert.
(3) After assuring that all 4 installed
vertical fin potted inserts are undamaged,
install the correct washers in accordance
with step 9.d. of the Accomplishment
Instructions of the ASB.
(h) This AD revises the helicopter
maintenance manual by adding an inspection
of the torque on the vertical fin attaching
hardware, and inspections of the vertical fin
and vertical fin support, to the 100-hour TIS
and annual scheduled inspections.
(i) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Regulations and
Policy Group, FAA, ATTN: Sharon Miles,
Aviation Safety Engineer, FAA, Rotorcraft
Directorate, Regulations and Policy Group,
Fort Worth, Texas 76193–0111, telephone
VerDate Aug<31>2005
17:25 Jul 12, 2007
Jkt 211001
(817) 222–5122, fax (817) 222–5961, for
information about previously approved
alternative methods of compliance.
Note: The subject of this AD is addressed
in Transport Canada (Canada) AD No. CF–
2006–12, dated June 5, 2006.
Issued in Fort Worth, Texas, on July 3,
2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. E7–13607 Filed 7–12–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28691; Directorate
Identifier 2006–SW–22–AD]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model AS355E, F, F1, F2, and
N Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
superseding an existing airworthiness
directive (AD) for the specified
Eurocopter France (ECF) helicopters.
That AD currently requires certain
checks of the magnetic chip detector
plug (chip detector) and the main
gearbox (MGB) oil-sight glass, certain
inspections of the lubrication pump
(pump), and replacing the MGB and the
pump with an airworthy MGB and
pump, if necessary. Also, the AD
requires that before an MGB or pump
with any hours time-in-service (TIS) can
be installed, it must meet the AD
requirements. This action would retain
those requirements but would add all
serial-numbered pumps to the
applicability. This proposal is prompted
by additional cases of MGB lubrication
pump deterioration and a further
investigation that determined that all
serial-numbered pumps might be
affected. The actions specified by the
proposed AD are intended to detect
sludge on the chip detector and dark oil
in the MGB, to prevent failure of the
MGB pump, seizure of the MGB, loss of
drive to an engine and main rotor, and
subsequent loss of control of the
helicopter.
Comments must be received on
or before September 11, 2007.
DATES:
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38529
Use one of the following
addresses to submit comments on this
proposed AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically;
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically;
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590;
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays; or
• Fax: 202–493–2251.
• You may get the service information
identified in this proposed AD from
American Eurocopter Corporation, 2701
Forum Drive, Grand Prairie, Texas
75053–4005, telephone (972) 641–3460,
fax (972) 641–3527.
You may examine the comments to
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Ed
Cuevas, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Safety
Management Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5355,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
Comments Invited
We invite you to submit any written
data, views, or arguments regarding this
proposed AD. Send your comments to
the address listed under the caption
ADDRESSES. Include the docket number
‘‘FAA–2007–28691, Directorate
Identifier 2006–SW–22–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed
rulemaking. Using the search function
of our docket Web site, you can find and
read the comments to any of our
dockets, including the name of the
individual who sent or signed the
comment. You may review the DOT’s
complete Privacy Act Statement in the
E:\FR\FM\13JYP1.SGM
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38530
Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules
Federal Register published on April 11,
2000 (65 FR 19477–78) or you may visit
https://dms.dot.gov.
jlentini on PROD1PC65 with PROPOSALS
Examining the Docket
You may examine the docket that
contains the proposed AD, any
comments, and other information in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located in Room
W12–140 on the ground floor of the
West Building at the street address
stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after the DMS receives
them.
Discussion
On May 24, 2006, we issued AD
2003–21–09 R1, Amendment 39–14621
(71 FR 31070, June 1, 2006), to revise
AD 2003–21–09. The revised AD
required the same actions as AD 2003–
21–09 but limited the applicability to
ECF helicopters with a pump, part
number (P/N) 355A32–0700–01, with a
serial number (S/N) 5731 or higher or
with a S/N below 5731 if the pump has
been overhauled or repaired after June
1, 1995. AD 2003–21–09 R1 was
prompted by an investigation that
revealed a malfunction occurred after
modifying the pump case on certain
pumps and after major overhaul and
repairs. The requirements of that AD
limited the applicability to certain
pumps and were intended to detect
sludge on the chip detector and dark oil
in the MGB, to prevent failure of the
MGB pump, seizure of the MGB, loss of
drive to an engine and main rotor, and
subsequent loss of control of the
helicopter.
Since issuing that AD, ECF has issued
Revision 1 to Alert Service Bulletin
(ASB) No. 05.00.40, dated January 5,
2006, which adds pumps, P/N 355A32–
0700–01, with a S/N SAR 1, SAR 2, or
SAR 5 to its effectivity. Also, Eurocopter
has issued Emergency ASB No.
05.00.40, Revision 2, dated December
20, 2006, which supersedes the
instructions in Revision 1 and extends
the effectivity of these instructions to all
serial-numbered pumps, P/N 355A32–
0700–01, 355A32–0700–02, and
355A32–0701–00. Revision 2 states that
a further incident of MGB pump
malfunction has been reported since the
original four cases and shows that the
machining modification of the earlier
pumps is not the only reason for early
deterioration of the oil pumps. The
DGAC classified these ASBs as
mandatory and issued AD No. F–2006–
027, Revision A, dated February 1, 2006,
VerDate Aug<31>2005
16:43 Jul 12, 2007
Jkt 211001
and Emergency AD No. 2006–0378–E,
effective December 27, 2006, which
supersedes and cancels AD No. F–2006–
027.
These helicopter models are
manufactured in France and are type
certificated for operation in the United
States under the provisions of 14 CFR
21.29 and the applicable bilateral
agreement. Pursuant to the applicable
bilateral agreement, the DGAC has kept
the FAA informed of the situation
described above. The FAA has
examined the findings of the DGAC,
reviewed all available information, and
determined that AD action is necessary
for products of these type designs that
are certificated for operation in the
United States.
This previously described unsafe
condition is likely to exist or develop on
other helicopters of the same type
designs. Therefore, the proposed AD
would supersede AD 2003–21–09 R1
and retain the requirements in that AD
but would also require adding pumps,
P/N 355A32–0700–01, 355A32–0700–
02, and 355A32–0701–00, any S/N, to
the applicability.
The FAA estimates that this proposed
AD would affect 84 helicopters of U.S.
registry, assuming they all have MGB
pumps with applicable S/Ns. It would
take about:
• 10 minutes to check the chip
detector and the MGB oil sight glass,
• 4 work hours to remove the MGB
and pump,
• 1 work hour to inspect the pump,
• 4 work hours to install a serviceable
MGB and pump at an average labor rate
of $80 per work hour, and
• $4,000 for an overhauled pump and
up to $60,000 for an overhauled MGB
per helicopter.
Based on these figures, we estimate
the revised total cost impact of the AD
on U.S. operators to be $355,920 per
year, assuming replacement of one
overhauled MGB and pump on one
helicopter per year and a daily check on
all helicopters for 260 days per year.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. Additionally, 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;
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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.
We prepared a draft economic
evaluation of the estimated costs to
comply with this proposed AD. See the
DMS to examine the draft economic
evaluation.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration proposes to amend part
39 of the Federal Aviation Regulations
(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. Section 39.13 is amended by
removing Amendment 39–14621 (71 FR
31070, June 1, 2006), and by adding a
new airworthiness directive (AD), to
read as follows:
Eurocopter France: Docket No. FAA–2007–
28691; Directorate Identifier 2006–SW–
22–AD. Supersedes AD 2003–21–09 R1,
Amendment 39–14621, Docket No.
2003–SW–10–AD.
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Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules
VerDate Aug<31>2005
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this visual check and must enter compliance
into the aircraft maintenance records in
accordance with 14 CFR 43.11 and
91.417(a)(2)(v). ‘‘Sludge’’ is a deposit on the
chip detector that is typically dark in color
and in the form of a film or paste, as
compared to metal chips or particles
normally found on a chip detector. Sludge
may have both metallic or nonmetallic
properties, may consist of copper (pinion
bearing), magnesium (pump case), and steel
(pinion) from the oil pump, and a
nonmetallic substance from the chemical
breakdown of the oil as it interacts with the
metal.
(b) Before further flight, if any sludge is
found on the chip detector, remove, open,
and inspect the pump.
(c) Before further flight, if the oil appears
dark in color when it is observed through the
MGB oil-sight glass, take an oil sample. If the
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oil taken in the sample is dark or dark
purple, before further flight, remove, open,
and inspect the pump.
Note 1: Eurocopter France Alert Service
Bulletin (ASB) No. 05.00.40, Revision 1,
dated January 5, 2006, and Emergency ASB
No. 05.00.40, Revision 2, dated December 20,
2006, pertain to the subject of this AD.
(d) While inspecting the pump, if you find
any of the following, replace the MGB and
the pump with an airworthy MGB and pump
before further flight:
(1) Crank pin play,
(2) Out of round bronze bushing in area
‘‘A’’ of Figure 1 of this AD,
(3) Offset of the driven gear pinion,
(4) Metal chips, or
(5) Wear in area ‘‘C’’ of Figure 1 of this AD.
BILLING CODE 4910–13–P
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jlentini on PROD1PC65 with PROPOSALS
Applicability: Model AS355E, F, F1, F2,
and N helicopters, with a main gear box
(MGB) lubrication pump (pump), part
number (P/N) 355A32–0700–01, 355A32–
0700–02, or 355A32–0701–00, any serial
number (S/N), certificated in any category.
Compliance: Required as indicated, unless
accomplished previously.
To detect sludge on the chip detector and
dark oil in the MGB, to prevent failure of the
MGB pump, seizure of the MGB, loss of drive
to an engine and main rotor, and subsequent
loss of control of the helicopter, do the
following:
(a) Before the first flight of each day and
at intervals not to exceed 10 hours time-inservice (TIS), check the MGB magnetic chip
detector plug (chip detector) for any sludge.
Also, check for dark oil in the MGB oil-sight
glass. An owner/operator (pilot) holding at
least a private pilot certificate may perform
38531
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Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules
Note 2: If wear is present in the B area
only, as depicted in Figure 1, replacing the
MGB and the pump is not required.
(e) Before replacing an MGB with a pump
to which this AD applies, accomplish the
requirements of paragraphs (a), (b), and (c) of
this AD.
(f) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Safety
Management Group, Rotorcraft Directorate,
FAA, ATTN: Ed Cuevas, Fort Worth, Texas
76193–0111, telephone (817) 222–5355, fax
(817) 222–5961, for information about
previously approved alternative methods of
compliance.
Note 3: The subject of this AD is addressed
in Direction Generale De L’Aviation Civile
(France) AD No. F–2006–027, dated February
1, 2006, and Emergency AD No. 2006–0378–
E, dated December 21, 2006.
[Docket No. FAA–2007–28689; Directorate
Identifier 2006–SW–17–AD]
Use one of the following
addresses to submit comments on this
proposed AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically;
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically;
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590;
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays; or
• Fax: (202) 493–2251.
You may get the service information
identified in this proposed AD from
FreeFlight Systems, 3700 IH 35, Waco,
Texas, USA, 76706, or by calling (254)
662–0000.
You may examine the comments to
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT:
Sung-Hui Cavazos, Aviation Safety
Engineer, FAA, Rotorcraft Directorate,
Special Certification Office, Fort Worth,
Texas 76193–0170, telephone (817)
222–5142, fax (817) 222–5785.
SUPPLEMENTARY INFORMATION:
RIN 2120–AA64
Comments Invited
Issued in Fort Worth, Texas, on July 2,
2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. E7–13624 Filed 7–12–07; 8:45 am]
BILLING CODE 4910–13–C
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; Trimble or
FreeFlight Systems 2101 I/O Approach
Plus Global Positioning System (GPS)
Navigation Systems
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
jlentini on PROD1PC65 with PROPOSALS
AGENCY:
SUMMARY: This document proposes
adopting a new airworthiness directive
(AD) for the Trimble or FreeFlight
Systems 2101 I/O Approach Plus global
positioning system (GPS) navigation
system (2101 I/O Approach Plus
system). The AD would require a
software upgrade for this system. This
proposal is prompted by an incident
that led to the discovery of several
annunciation errors with the 2101 I/O
Approach Plus system. The actions
specified by the proposed AD are
intended to prevent a pilot from making
an unsafe decision based on erroneous
information provided by the 2101 I/O
Approach Plus system, which could
result in loss of control of the aircraft.
DATES: Comments must be received on
or before September 11, 2007.
VerDate Aug<31>2005
16:43 Jul 12, 2007
Jkt 211001
ADDRESSES:
We invite you to submit any written
data, views, or arguments regarding this
proposed AD. Send your comments to
the address listed under the caption
ADDRESSES. Include the docket number
‘‘FAA–2007–28689, Directorate
Identifier 2006–SW–17–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed
rulemaking. Using the search function
of our docket web site, you can find and
read the comments to any of our
dockets, including the name of the
individual who sent or signed the
comment. You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
PO 00000
Frm 00037
Fmt 4702
Sfmt 4702
2000 (65 FR 19477–78) or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the docket that
contains the proposed AD, any
comments, and other information in
person at the Docket Management
System (DMS) Docket Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone 1–800–647–
5527) is located in Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC. Comments will be
available in the AD docket shortly after
the DMS receives them.
Discussion
This document proposes adopting a
new AD for the 2101 I/O Approach Plus
system that would require a software
upgrade. This proposal is prompted by
an incident involving a Federal
Republic of Germany military helicopter
that led to the discovery of the following
system malfunctions:
• Under certain conditions, when the
system enters Dead Reckoning (DR)
mode, the navigation and Super flags
are removed from the display; however,
the DR message and associated message
light annunciation may fail to
illuminate;
• The navigation and Super flags may
not be removed from the display as
required during approach mode after
loss of a Receiver Autonomous Integrity
Monitor (RAIM) condition; and
• When a RAIM error occurs (detects
a satellite failure) and the system is
unable to exclude the affected satellite,
the unit may fail to enter DR mode and
may fail to remove the navigation and
Super flags from the display.
These malfunctions could result in
the following unsafe conditions:
• System could fail when interfaced
with Terrain Awareness Warning
System (TAWS) and the TAWS can fail
to annunciate terrain alerts;
• System could provide misleading
heading information; or
• System may provide erroneous
navigation fault annunciations.
The actions specified by the proposed
AD are intended to prevent a pilot from
making an unsafe decision based on
erroneous information provided by the
2101 I/O Approach Plus system, which
could result in loss of control of the
aircraft.
These unsafe conditions are likely to
exist or develop on any aircraft with a
2101 I/O Approach Plus system
installed. Therefore, the proposed AD
would require, within 180 days after the
effective date of the AD for aircraft
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]]>Agencies
[Federal Register Volume 72, Number 134 (Friday, July 13, 2007)]
[Proposed Rules]
[Pages 38529-38532]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13624]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28691; Directorate Identifier 2006-SW-22-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS355E, F, F1,
F2, and N Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes superseding an existing airworthiness
directive (AD) for the specified Eurocopter France (ECF) helicopters.
That AD currently requires certain checks of the magnetic chip detector
plug (chip detector) and the main gearbox (MGB) oil-sight glass,
certain inspections of the lubrication pump (pump), and replacing the
MGB and the pump with an airworthy MGB and pump, if necessary. Also,
the AD requires that before an MGB or pump with any hours time-in-
service (TIS) can be installed, it must meet the AD requirements. This
action would retain those requirements but would add all serial-
numbered pumps to the applicability. This proposal is prompted by
additional cases of MGB lubrication pump deterioration and a further
investigation that determined that all serial-numbered pumps might be
affected. The actions specified by the proposed AD are intended to
detect sludge on the chip detector and dark oil in the MGB, to prevent
failure of the MGB pump, seizure of the MGB, loss of drive to an engine
and main rotor, and subsequent loss of control of the helicopter.
DATES: Comments must be received on or before September 11, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically;
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically;
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590;
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
Fax: 202-493-2251.
You may get the service information identified in this
proposed AD from American Eurocopter Corporation, 2701 Forum Drive,
Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972)
641-3527.
You may examine the comments to this proposed AD in the AD docket
on the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas
76193-0111, telephone (817) 222-5355, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2007-
28691, Directorate Identifier 2006-SW-22-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed rulemaking. Using the search
function of our docket Web site, you can find and read the comments to
any of our dockets, including the name of the individual who sent or
signed the comment. You may review the DOT's complete Privacy Act
Statement in the
[[Page 38530]]
Federal Register published on April 11, 2000 (65 FR 19477-78) or you
may visit https://dms.dot.gov.
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Operations
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Operations office (telephone (800) 647-5527) is
located in Room W12-140 on the ground floor of the West Building at the
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
On May 24, 2006, we issued AD 2003-21-09 R1, Amendment 39-14621 (71
FR 31070, June 1, 2006), to revise AD 2003-21-09. The revised AD
required the same actions as AD 2003-21-09 but limited the
applicability to ECF helicopters with a pump, part number (P/N) 355A32-
0700-01, with a serial number (S/N) 5731 or higher or with a S/N below
5731 if the pump has been overhauled or repaired after June 1, 1995. AD
2003-21-09 R1 was prompted by an investigation that revealed a
malfunction occurred after modifying the pump case on certain pumps and
after major overhaul and repairs. The requirements of that AD limited
the applicability to certain pumps and were intended to detect sludge
on the chip detector and dark oil in the MGB, to prevent failure of the
MGB pump, seizure of the MGB, loss of drive to an engine and main
rotor, and subsequent loss of control of the helicopter.
Since issuing that AD, ECF has issued Revision 1 to Alert Service
Bulletin (ASB) No. 05.00.40, dated January 5, 2006, which adds pumps,
P/N 355A32-0700-01, with a S/N SAR 1, SAR 2, or SAR 5 to its
effectivity. Also, Eurocopter has issued Emergency ASB No. 05.00.40,
Revision 2, dated December 20, 2006, which supersedes the instructions
in Revision 1 and extends the effectivity of these instructions to all
serial-numbered pumps, P/N 355A32-0700-01, 355A32-0700-02, and 355A32-
0701-00. Revision 2 states that a further incident of MGB pump
malfunction has been reported since the original four cases and shows
that the machining modification of the earlier pumps is not the only
reason for early deterioration of the oil pumps. The DGAC classified
these ASBs as mandatory and issued AD No. F-2006-027, Revision A, dated
February 1, 2006, and Emergency AD No. 2006-0378-E, effective December
27, 2006, which supersedes and cancels AD No. F-2006-027.
These helicopter models are manufactured in France and are type
certificated for operation in the United States under the provisions of
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the
applicable bilateral agreement, the DGAC has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
DGAC, reviewed all available information, and determined that AD action
is necessary for products of these type designs that are certificated
for operation in the United States.
This previously described unsafe condition is likely to exist or
develop on other helicopters of the same type designs. Therefore, the
proposed AD would supersede AD 2003-21-09 R1 and retain the
requirements in that AD but would also require adding pumps, P/N
355A32-0700-01, 355A32-0700-02, and 355A32-0701-00, any S/N, to the
applicability.
The FAA estimates that this proposed AD would affect 84 helicopters
of U.S. registry, assuming they all have MGB pumps with applicable S/
Ns. It would take about:
10 minutes to check the chip detector and the MGB oil
sight glass,
4 work hours to remove the MGB and pump,
1 work hour to inspect the pump,
4 work hours to install a serviceable MGB and pump at an
average labor rate of $80 per work hour, and
$4,000 for an overhauled pump and up to $60,000 for an
overhauled MGB per helicopter.
Based on these figures, we estimate the revised total cost impact
of the AD on U.S. operators to be $355,920 per year, assuming
replacement of one overhauled MGB and pump on one helicopter per year
and a daily check on all helicopters for 260 days per year.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, 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 draft economic evaluation of the estimated costs to
comply with this proposed AD. See the DMS to examine the draft economic
evaluation.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by removing Amendment 39-14621 (71 FR
31070, June 1, 2006), and by adding a new airworthiness directive (AD),
to read as follows:
Eurocopter France: Docket No. FAA-2007-28691; Directorate Identifier
2006-SW-22-AD. Supersedes AD 2003-21-09 R1, Amendment 39-14621,
Docket No. 2003-SW-10-AD.
[[Page 38531]]
Applicability: Model AS355E, F, F1, F2, and N helicopters, with
a main gear box (MGB) lubrication pump (pump), part number (P/N)
355A32-0700-01, 355A32-0700-02, or 355A32-0701-00, any serial number
(S/N), certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect sludge on the chip detector and dark oil in the MGB,
to prevent failure of the MGB pump, seizure of the MGB, loss of
drive to an engine and main rotor, and subsequent loss of control of
the helicopter, do the following:
(a) Before the first flight of each day and at intervals not to
exceed 10 hours time-in-service (TIS), check the MGB magnetic chip
detector plug (chip detector) for any sludge. Also, check for dark
oil in the MGB oil-sight glass. An owner/operator (pilot) holding at
least a private pilot certificate may perform this visual check and
must enter compliance into the aircraft maintenance records in
accordance with 14 CFR 43.11 and 91.417(a)(2)(v). ``Sludge'' is a
deposit on the chip detector that is typically dark in color and in
the form of a film or paste, as compared to metal chips or particles
normally found on a chip detector. Sludge may have both metallic or
nonmetallic properties, may consist of copper (pinion bearing),
magnesium (pump case), and steel (pinion) from the oil pump, and a
nonmetallic substance from the chemical breakdown of the oil as it
interacts with the metal.
(b) Before further flight, if any sludge is found on the chip
detector, remove, open, and inspect the pump.
(c) Before further flight, if the oil appears dark in color when
it is observed through the MGB oil-sight glass, take an oil sample.
If the oil taken in the sample is dark or dark purple, before
further flight, remove, open, and inspect the pump.
Note 1: Eurocopter France Alert Service Bulletin (ASB) No.
05.00.40, Revision 1, dated January 5, 2006, and Emergency ASB No.
05.00.40, Revision 2, dated December 20, 2006, pertain to the
subject of this AD.
(d) While inspecting the pump, if you find any of the following,
replace the MGB and the pump with an airworthy MGB and pump before
further flight:
(1) Crank pin play,
(2) Out of round bronze bushing in area ``A'' of Figure 1 of
this AD,
(3) Offset of the driven gear pinion,
(4) Metal chips, or
(5) Wear in area ``C'' of Figure 1 of this AD.
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[GRAPHIC] [TIFF OMITTED] TP13JY07.000
[[Page 38532]]
Note 2: If wear is present in the B area only, as depicted in
Figure 1, replacing the MGB and the pump is not required.
(e) Before replacing an MGB with a pump to which this AD
applies, accomplish the requirements of paragraphs (a), (b), and (c)
of this AD.
(f) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Safety Management Group, Rotorcraft
Directorate, FAA, ATTN: Ed Cuevas, Fort Worth, Texas 76193-0111,
telephone (817) 222-5355, fax (817) 222-5961, for information about
previously approved alternative methods of compliance.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD No. F-2006-027, dated
February 1, 2006, and Emergency AD No. 2006-0378-E, dated December
21, 2006.
Issued in Fort Worth, Texas, on July 2, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-13624 Filed 7-12-07; 8:45 am]
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