[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.
------------------------------------------------------------------------
                       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