Document ID: FAA-2004-19559-0011
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Rolls-Royce plc RB211 Trent 700 Series Turbofan Engines
Posted Date: 2009-10-26T04:00Z

[Federal Register: October 26, 2009 (Volume 74, Number 205)]
[Proposed Rules]               
[Page 54940-54943]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26oc09-12]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-19559; Directorate Identifier 2004-NE-03-AD]
RIN 2120-AA64

 
Airworthiness Directives; Rolls-Royce plc RB211 Trent 700 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 plc (RR) RB211 Trent 700 series turbofan 
engines. That AD currently requires initial and repetitive borescope 
inspections of the high pressure-and-intermediate pressure (HP-IP) 
turbine internal and external oil vent tubes for coking and carbon 
buildup, and cleaning or replacing the vent tubes if necessary. This 
proposed AD would require the same actions, but would add additional 
inspections of the vent flow restrictor. This proposed AD results from 
further analysis that the cleaning of the vent tubes required by AD 
2007-02-05 could lead to loosened carbon fragments, causing a blockage 
downstream in the vent flow restrictor. We are proposing this AD to 
prevent internal oil fires due to coking and carbon buildup that could 
cause uncontained engine failure and damage to the airplane.

DATES: We must receive any comments on this proposed AD by December 28, 
2009.

[[Page 54941]]

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.
    Contact Rolls-Royce plc, P.O. Box 31, Derby, England; telephone: 
011-44-1332-249428; fax: 011-44-1332-249223, for the service 
information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-7199.

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-2005-
19559; Directorate Identifier 2004-NE-03-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 based on those comments.
    We will post all comments we receive, without change, to http://
www.regulations.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 Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, 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).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is the same as 
the Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

Discussion

    On January 12, 2007, the FAA issued AD 2007-02-05, Amendment 39-
14892 (72 FR 2603, January 22, 2007). The European Aviation Safety 
Agency (EASA), which is the Technical Agent for the Member States of 
the European Community, notified us that an unsafe condition may exist 
on RB211 Trent 700 series turbofan engines. Since AD 2007-02-05 was 
issued, EASA advises that further analysis has now identified that 
previous intervention actions may have exacerbated the problem of 
carbon formation in the vent pipe. These intervention actions are 
believed to loosen carbon fragments which are subsequently released 
during engine operation, leading to blockage downstream in the vent 
flow restrictor. The resultant reduced vent pipe flow will then cause 
accelerated carbon buildup inside the pipe and increased likelihood of 
an internal oil fire.

Relevant Service Information

    We have reviewed and approved the technical contents of Rolls-Royce 
plc Alert Service Bulletin (ASB) No. RB.211-72-AE302, Revision 7, dated 
April 30, 2009. That ASB describes procedures for borescope inspections 
of the HP-IP turbine internal and external oil vent tubes for coking 
and carbon buildup, and cleaning or replacing the vent tubes if 
necessary. That ASB also describes procedures for visual inspections of 
the vent pipe restrictor immediately after pipe cleaning and a high-
power engine run. For internal oil vent tubes to pass inspection, they 
must allow cleaning tool, number HU80298, to pass through them. EASA 
classified this service bulletin as mandatory and issued AD 2007-0201 
and AD 2007-0202 (corrected August 8, 2007), to ensure the 
airworthiness of these RB211 Trent 700 series turbofan engines in 
Europe.

Bilateral Agreement Information

    This engine model is manufactured in the United Kingdom and is type 
certificated for operation in the United States under the provisions of 
Section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Under this bilateral 
airworthiness agreement, EASA kept us informed of the situation 
described above. We have examined the findings of the EASA, reviewed 
all available information, and determined that AD action is necessary 
for products of this type design that are certificated for operation in 
the United States.

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 require 
initial and repetitive borescope inspections of the HP-IP turbine 
internal and external oil vent tubes for coking and carbon buildup, and 
cleaning or replacing the vent tubes if necessary. This proposed AD 
would also require visual inspections of the vent flow restrictor 
immediately after pipe cleaning and a high-power engine run. We are 
issuing this AD to prevent internal oil fires due to coking and carbon 
buildup that could cause uncontained engine failure and damage to the 
airplane. The proposed AD would require that you do these actions using 
the service information described previously.

Table 1 Clarification

    We found it necessary to clarify the second sentence in the first 
column of the Initial Inspection Table 1, which we carried forward from 
AD 2007-02-05. We changed ``Has fewer than 10,000 hours TSN or fewer 
than 2,500 CSN on the effective date of this AD'' to ``Has fewer than 
10,000 hours TSN and fewer than 2,500 CSN on the effective date of this 
AD.''

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 33 engines of U.S. registry. We also estimate that 
it would take about one work-hour per engine to comply with this 
proposed AD. The average labor rate is $80 per work-hour. Required 
parts would cost about $2,000 per engine. Based on these figures, we 
estimate the cost of the proposed AD on U.S. operators to be $68,640.

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

[[Page 54942]]

detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 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, Incorporation by 
reference, 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 39-14892 (72 FR 
2603, January 22, 2007) and by adding a new airworthiness directive, to 
read as follows:

Rolls-Royce plc: Docket No. FAA-2005-19559; Directorate Identifier 
2004-NE-03-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by December 28, 
2009.

Affected ADs

    (b) This AD supersedes AD 2007-02-05, Amendment 39-14892.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 768-60, 
RB211 Trent 772-60, and RB211 Trent 772B-60 series turbofan engines. 
These engines are installed on, but not limited to, Airbus A330-243, 
-341, -342 and -343 series airplanes.

Unsafe Condition

    (d) This AD results from further analysis that the cleaning of 
the vent tubes required by AD 2007-02-05 could lead to loosened 
carbon fragments, causing a blockage downstream in the vent flow 
restrictor. We are issuing this AD to prevent internal oil fires due 
to coking and carbon buildup that could cause uncontained engine 
failure and damage to the airplane.

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.

Initial Inspections, Cleaning, and Replacements

    (f) Using the schedule in Table 1 of this AD, borescope-inspect 
and clean as necessary, the high pressure-and-intermediate pressure 
(HP-IP) turbine internal oil vent tubes, external oil vent tubes, 
and bearing chamber.

                  Table 1--Initial Inspection Schedule
------------------------------------------------------------------------
    If the engine or the 05 module:          Then initially inspect:
------------------------------------------------------------------------
Has reached 10,000 hours time-since-new  Within 3 months after the
 (TSN) or reached 2,500 cycles-since-     effective date of this AD.
 new (CSN) on the effective date of
 this AD.
Has fewer than 10,000 hours TSN and      Within 3 months after reaching
 fewer than 2,500 CSN on the effective    10,000 hours TSN or 2,500 CSN,
 date of this AD.                         whichever occurs first.
Is returned for an engine shop visit...  Before returning to service.
------------------------------------------------------------------------

     (1) If after cleaning, there is still carbon in the vent tube 
that prevents cleaning tool number HU80298 from passing through the 
tube, then replace the internal oil vent tube within 10 cycles-in-
service (CIS).
    (2) If after cleaning, there is still carbon of visible 
thickness in either of the two external oil vent tubes, then replace 
the external oil vent tube before further flight.
    (3) Use paragraphs 3.A. through 3.A.(7) of the Accomplishment 
Instructions of RR Alert Service Bulletin (ASB) No. RB.211-72-AE302, 
Revision 7, dated April 30, 2009, to do the borescope inspections 
and cleaning of the oil vent tubes and bearing chamber.

Initial Visual Inspection of the Vent Flow Restrictor

    (g) For engines that, on the effective date of this AD, have not 
accumulated 25 service cycles since the last cleaning and 
inspection, visually inspect the vent flow restrictor either after a 
high-power ground run or within 25 service cycles of the last 
cleaning and inspection.
    (h) For engines that, on the effective date of this AD, have 
accumulated 25 or more service cycles since the last cleaning and 
inspection, visually inspect the vent flow restrictor either after a 
high-power ground run or within 25 service cycles after the 
effective date of this AD.
    (i) Use paragraph 3.A.(8) of the Accomplishment Instructions of 
RR ASB No. RB.211-72-AE302, Revision 7, dated April 30, 2009, to do 
the visual inspections.

Repetitive Inspections, Cleaning, and Replacements

    (j) Within 6,400 hours time-in-service since last inspection and 
cleaning, or within 1,600 cycles-since-last inspection and cleaning, 
or at the next engine shop visit, whichever occurs first, borescope-
inspect the HP-IP turbine internal and external oil vent tubes and 
bearing chamber, and clean the oil vent tubes as necessary.
    (1) If after cleaning there is still carbon in the internal oil 
vent tube that prevents cleaning tool, number HU80298, from passing 
through the tube, then replace the internal oil vent tube within 10 
CIS.
    (2) If after cleaning there is still carbon of visible 
thickness, in either of the two external oil vent tubes, then 
replace the external oil vent tube before further flight.
    (3) Use paragraphs 3.A. through 3.A.(7) of the Accomplishment 
Instructions of RR ASB No. RB.211-72-AE302, Revision 7, dated April 
30, 2009, to do the borescope inspections and cleaning of the oil 
vent tubes and bearing chamber.

[[Page 54943]]

    (k) Visually inspect the vent flow restrictor either after a 
high-power ground run or within 25 service cycles after performing 
the cleaning and inspection specified in paragraph (f) through 
(f)(3) of this AD. Use paragraph 3.A.(8) of the Accomplishment 
Instructions of RR ASB No. RB.211-72-AE302, Revision 7, dated April 
30, 2009, to do the visual inspection.

Definition

    (l) For the purpose of this AD, an engine shop visit is 
induction of the engine into the engine shop for any cause.

Alternative Methods of Compliance

    (m) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD, if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (n) European Aviation Safety Agency AD 2007-0201, dated August 
1, 2007, and AD 2007-0202 (corrected August 8, 2007), also address 
the subject of this AD. Rolls-Royce plc ASB No. RB.211-72-AE302, 
Revision 7, dated April 30, 2009, pertains to the subject of this 
AD. Contact Rolls-Royce plc, P.O. Box 31, Derby, England; telephone: 
011-44-1332-249428; fax: 011-44-1332-249223, for the service 
information identified in this AD.
    (o) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on October 16, 2009.
Robert J. Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-25645 Filed 10-23-09; 8:45 am]

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