[Federal Register Volume 72, Number 60 (Thursday, March 29, 2007)]
[Proposed Rules]
[Pages 14724-14727]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-5775]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-26966; Directorate Identifier 99-NE-01-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation AE 3007A and AE
3007C Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for Rolls-Royce Corporation (RRC) AE 3007A and AE 3007C
series turbofan engines. That AD currently prohibits any flight
following a ground engine start where the engine oil temperature is
below 32 [deg]F (0 [deg]C), unless certain preflight operational
procedures are followed. This proposed AD would also require those
actions, and would also require a terminating action. This proposed AD
would supersede the compliance requirements of AD 99-02-51 and all
related alternative methods of compliance (AMOCs). This proposed AD
results from design improvements to components in the accessory gearbox
air turbine starter mounting pad. We are proposing this AD to prevent
an in-flight engine shutdown due to loss of engine oil from the starter
shaft seal.
DATES: We must receive any comments on this proposed AD by May 29,
2007.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN
46206; telephone (317) 230-3774; fax (317) 230-8084; e-mail:
royce.com">indy.pubs.services@rolls-royce.com, to get the service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Kyri Zaroyiannis, Aerospace Engineer,
Chicago Aircraft Certification Office, Small Airplane Directorate, FAA,
2300 E. Devon Ave., Des Plaines, IL 60018; telephone (847) 294-7836;
fax (847) 294-7834.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-
[[Page 14725]]
2007-26966; Directorate Identifier 99-NE-01-AD'' in the subject line 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 http://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 AD. Using the search function of the
DMS Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78) or you
may visit http://dms.dot.gov.
Examining the AD Docket
You may examine the docket that contains the proposal, any comments
received and any final disposition in person at the Docket Management
Facility between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The Docket Office (telephone (800) 647-5227) is
located on the plaza level of the Department of Transportation Nassif
Building at the street address stated in ADDRESSES. Comments will be
available in the AD docket shortly after the DMS receives them.
Docket Number Change
We are transferring the docket for this proposed AD to the Docket
Management System as part of our on-going docket management
consolidation efforts. The new Docket No. is FAA-2007-26966. The old
Docket No. became the Directorate Identifier, which is 99-NE-01-AD.
Discussion
On March 29, 1999, we issued AD 99-02-51, Amendment 39-11108 (64 FR
16339, April 5, 1999), applicable to RRC AE 3007A and AE 3007C series
turbofan engines. That AD prohibits any flight following a ground
engine start where the engine oil temperature is below 32 [deg]F (0
[deg]C), unless certain preflight operational procedures are followed
to ensure that there is no excessive loss of oil from leakage at the
air turbine starter shaft. That action resulted from reports of in-
flight engine shutdowns attributed to loss of engine oil from the
starter shaft seal.
Since we issued AD 99-02-51, RRC, Cessna Aircraft Company, and
Empresa Brasileira de Aeronautica S.A. (EMBRAER) issued Service
Bulletins (SBs) that describe a procedure to install a cap on the
accessory gearbox starter pad drain fitting to prevent rapid engine oil
loss during flight. These SBs were approved in 1999 as AMOCs to the
requirements of AD 99-02-51. In September 2001, RRC developed single-
and multi-orifice restrictors that were approved for use also as an
AMOC that replaced the drain fitting cap in the previous AMOCs. RRC has
since improved the design for the multi-orifice restrictor which is
also approved as an AMOC. Since we approved these AMOCs, RRC released
an improved seal for the accessory gearbox air turbine starter mounting
pad. On January 19, 2006, we approved a terminating action AMOC
incorporating the improved seal. That AMOC requires no cap or
restrictor on the starter drain, but does not require removal of those
components either. This proposed AD would mandate the removal of the
AMOC configurations incorporating caps or restrictors and the
installation of an open drain adapter.
Relevant Service Information
We have reviewed and approved the technical contents of the
following RRC SBs:
SB No. AE 3007A-72-321 AE 3007C-72-250, Revision 2, which
describes procedures for installing an improved starter shaft seal.
SB No. AE 3007C-72-223, Revision 1, and SB No. AE 3007A-
72-330, Revision 1, which describe procedures for installing an open
starter drain adapter.
SB No. AE 3007A-72-274, Revision 1, which describes
procedures for removing the drain cap or starter drain adapter on AE
3007A series engines.
The SB issue dates do not appear in this proposed AD because we
agreed to allow RRC to assign the final rule AD issue date to them, as
they want to reference the AD number in the SBs.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would:
Prohibit before further flight, any flight following a
ground engine start where the engine oil temperature is below 32 [deg]F
(0 [deg]C), unless certain preflight operational procedures are
followed to ensure that there is no excessive loss of oil from leakage
at the air turbine starter shaft; and
Require terminating action to the prohibition requirements
of the existing AD, by removing from service certain seal P/Ns from the
accessory gearbox air turbine starter mounting pad and installing an
improved seal; and
Require removing certain P/N drain caps, drain adapters,
and orifice inserts, and installing an open adapter on the starter pad
drain.
The proposed AD would require that you do these actions using the
service information described previously.
Costs of Compliance
We estimate that this proposed AD would affect 1,868 RRC AE 3007A
and AE 3007C series turbofan engines installed on aircraft of U.S.
registry. We also estimate that it would take about 4 work-hours per
engine to perform the proposed terminating action, and that the average
labor rate is $80 per work-hour. Required parts would cost about $2,917
per engine. Based on these figures, if all engines incorporated the
terminating action, we estimate the total cost of the proposed AD to
U.S. operators to be $6,046,100.
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
[[Page 14726]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed AD:
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. Would 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. 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration 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 39-11108 (64 FR
16339, April 5, 1999) and by adding a new airworthiness directive to
read as follows:
Rolls-Royce Corporation (formerly Allison Engine Company, Inc.):
Docket No. FAA-2007-26966; Directorate Identifier 99-NE-01-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by May 29,
2007.
Affected ADs
(b) This AD supersedes AD 99-02-51, Amendment 39-11108.
Applicability
(c) This AD applies to Rolls-Royce Corporation (RRC) (formerly
Allison Engine Company, Inc.) AE 3007A and AE 3007C series turbofan
engines. These engines are installed on, but not limited to, Cessna
Aircraft Company 750 series, and Empresa Brasileira de Aeronautica
S. A. (EMBRAER) EMB-135 and EMB-145 series airplanes.
Unsafe Condition
(d) This AD results from design improvements to components in
the accessory gearbox air turbine starter mounting pad. We are
issuing this AD to prevent an in-flight engine shutdown due to loss
of engine oil from the starter shaft seal.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Prohibited Flights
(f) All flights after ground engine starts at engine oil
temperatures below 32 [deg]F (0 [deg]C), are prohibited except as
follows:
(1) If the engine oil temperature has dropped below 32 [deg]F (0
[deg]C), before flight, perform a high-power leak check on each
engine (at least three minutes at takeoff power).
(2) Oil consumption greater than 0.32 quart per hour (303 cc per
hour) is not permitted. Instructions for performing the high-power
leak check for the AE 3007A series engines can be found in the
Rolls-Royce AE 3007A Series Maintenance Manual, TASK 72-00-00-700-
801, SUBTASK 72-00-00-790-002. Leak check limits for the AE 3007A
series engines can be found in the Rolls-Royce AE 3007A Series
Maintenance Manual, TASK 71-00-00-200-801.
(3) Instructions for performing the high-power leak check for
the AE 3007C series engines (including leak check limits) can be
found in the Rolls-Royce AE 3007C Series Maintenance Manual, TASK
72-00-00-700-801, SUBTASK 72-00-00-790-002.
Terminating Action
(g) No later than September 30, 2009, as terminating action to
the requirements in paragraph (f) through (f)(3) of this AD, do the
following, as applicable to your engine model and configuration:
(1) Remove seal part number (P/N) 42520-71, 42520-196-X, 99004-
1-6, 42520-75, or 42520-167, from the accessory gearbox (AGB) air
turbine starter mounting pad.
(2) Install a new seal, P/N AS3209-026, or other serviceable
part, to the shaft of the starter mounting pad.
(3) Install a new bearing locknut, P/N 42520-170, or other
serviceable part, and an AGB air turbine starter mounting pad
mechanical seal, P/N 42520-192, or other serviceable part.
(4) Use paragraphs 2. through 2.G. of the Accomplishment
Instructions of RRC Service Bulletin (SB) No. AE 3007A-72-321 / AE
3007C-72-250, Revision 2, to do the removals and installations.
(5) For AE 3007A series engines, remove the drain cap or starter
drain adapter. Use paragraphs 2. through 2.C.(4)(c) of the
Accomplishment Instructions of RRC SB No. AE 3007A-72-274, Revision
1, to do the removal.
(6) For AE 3007A series engines, install an open starter drain
adapter. Use paragraphs 2. through 2.C.(2) of the Accomplishment
Instructions of RRC SB No. AE 3007A-72-330, Revision 1, to do the
installation.
(7) For AE 3007C series engines, install an open starter drain
adapter. Use paragraphs 2. through 2.E.(2) of the Accomplishment
Instructions of RRC SB No. AE 3007C-72-223, Revision 1, to do the
installation.
Definition
(h) A serviceable part is any FAA-approved part not being
removed from service, or not otherwise specifically addressed by
this AD action. Serviceable parts may be available from the original
equipment manufacturer or through Part Manufacturer Approval
sources.
Prohibition of Seals
(i) Once the terminating action in this AD is performed on an
engine, seal P/Ns 42520-71, 42520-196-X, 99004-1-6, 42520-75, and
42520-167, are prohibited from being installed on the air starter
mounting pad.
Previous Credit
(j) Previous credit is allowed for the terminating action in
paragraphs (g)(1) through (g)(7) of this AD, that was done using the
Accomplishment Instructions of the SBs listed in the following Table
1, before the effective date of this AD:
Table 1.--SBs Allowing Previous Credit
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For AE 3007A Series Engines
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(1) Engine--Accessory Drive Gearbox Assembly--New Starter Shaft Seal;
RRC SB No. AE 3007A-72-321/AE 3007C-72-250, Revision 1, dated November
7, 2005; and
(2) Engine--Accessory Gearbox Starter Pad Drain--Remove The Drain Cap or
Starter Drain Adapter; RRC SB No. AE 3007A-72-274, dated January 19,
2006; and
(3) Engine--Accessory Gearbox Starter Pad Drain--Install the Open
Starter Drain Adapter (23083402 or 23077526); RRC SB No. AE 3007A-72-
330, dated January 19, 2006.
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For AE 3007C Series Engines
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(4) Engine--Accessory Drive Gearbox Assembly--New Starter Shaft Seal;
RRC SB No. AE 3007A-72-321/AE 3007C-72-250, Revision 1, dated November
7, 2005; and
[[Page 14727]]
(5) Engine--Accessory Gearbox Starter Pad Drain--Install the Open
Starter Drain Adapter (23077526 or 23083403); RRC SB No. AE 3007C-72-
223, dated January 19, 2006.
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Alternative Methods of Compliance (AMOC)
(k) The Manager, Chicago Aircraft Certification Office, has the
authority to approve AMOCs for this AD if requested using the
procedures found in 14 CFR 39.19.
(l) AMOCs approved for AD 99-02-51 are not approved as AMOCs for
this AD.
Related Information
(m) Contact Kyri Zaroyiannis, Aerospace Engineer, Chicago
Aircraft Certification Office, Small Airplane Directorate, FAA, 2300
E. Devon Ave., Des Plaines, IL 60018; e-mail:
[email protected]; telephone (847) 294-7836; fax (847) 294-
7834, for more information about this AD.
Issued in Burlington, Massachusetts, on March 23, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E7-5775 Filed 3-28-07; 8:45 am]
BILLING CODE 4910-13-P