[Federal Register Volume 70, Number 33 (Friday, February 18, 2005)]
[Proposed Rules]
[Pages 8303-8305]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-3191]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 70, No. 33 / Friday, February 18, 2005 / 
Proposed Rules  

[[Page 8303]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-12-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 875, 877, 
884, 884B, 892, 892B, and 895 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 875, 877, 884, 892, 
892B, and 895 series turbofan engines. That AD currently requires 
repetitive application of dry film lubricant (DFL) to low pressure 
compressor (LPC) fan blade roots. This proposed AD would require the 
same actions but at more frequent intervals than the existing AD, add 
the Trent 884B engine to the list of engine models affected, add a fan 
blade part number (P/N) to the affected list of fan blades, and would 
relax the initial DFL repetitive application compliance time for 
certain fan blades that have never been removed from the disk. This 
proposed AD results from discovering DFL in worse condition than 
anticipated on fan blades fitted to disks previously run for a 
significant period. This proposed AD also results from the need to 
update the list of engine models affected, and to update the list of 
fan blade part numbers affected. We are proposing this AD to prevent 
LPC fan blade loss, which could result in an uncontained engine failure 
and possible aircraft damage.

DATES: We must receive any comments on this proposed AD by April 19, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     By mail: Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 2001-NE-12-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
     By fax: (781) 238-7055.
     By e-mail: [email protected].
    You may examine the AD docket, by appointment, at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone: (781) 238-7175, fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2001-NE-12--AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. If a person contacts us verbally, and that contact relates to a 
substantive part of this proposed AD, we will summarize the contact and 
place the summary in the docket. We will consider all comments received 
by the closing date and may amend the proposed AD in light of those 
comments.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Discussion

    On May 16, 2002, the FAA issued AD 2002-10-15, Amendment 39-12761 
(67 FR 36803, May 28, 2002). That AD requires repetitive application of 
DFL to LPC fan blade roots. That AD resulted from an aborted take-off 
resulting from LPC fan blade loss, and reports of four cracked LPC fan 
blade roots.

Actions Since AD 2002-10-15 was Issued

    Since that AD was issued, we have determined from a sampling of DFL 
coatings on fan blades, that the DFL coating condition has some 
variation. The condition appears worse than anticipated on fan blades 
fitted to disks previously run for a significant period. Also, since 
that AD was issued, we discovered that the Trent 884B engine needs to 
be added to the applicability list, and fan blade, P/N FW23552, needs 
to be added to the list of affected blades.

Special Flight Permits Paragraph Removed

    Paragraph (d) of the current AD, AD 2002-10-15, contains a 
paragraph pertaining to special flight permits. Even though this final 
rule does not contain a similar paragraph, we have made no changes with 
regard to the use of special flight permits to operate the airplane to 
a repair facility to do the work required by this AD. In July 2002, we 
published a new Part 39 that contains a general authority regarding 
special flight permits and airworthiness directives; see Docket No. 
FAA-2004-8460, Amendment 39-9474 (69 FR 47998, July 22, 2002). Thus, 
when we now supersede ADs we will not include a specific paragraph on 
special flight permits unless we want to limit the use of that general 
authority granted in section 39.23.

Replacement of References to Manual Tasks, Repair Schemes, and Coatings

    In this proposed AD, we have replaced references in AD 2002-10-15 
to Aircraft Maintenance Manual task 72-31-11-300-801-R00 (Repair Scheme 
FRS A031 by air spray method only), Engine Manual task 72-31-11-R001 
(Repair Scheme FRS A028), and lubricants, Dow Corning 321R (Rolls-Royce 
(RR) Omat item 4/51), Rocol Dry Moly Spray (RR Omat item 4/52), Molydag 
709 (RR Omat item 444), or PL.237/R1 (RR Omat item 4/43), with a 
reference to RR Alert Service Bulletin No. RB.211-72-AD347, Revision 6, 
dated April 22, 2004, which contains that information.

[[Page 8304]]

Bilateral Agreement Information

    These engine models are manufactured in the U.K. and are 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. Pursuant to this 
bilateral airworthiness agreement, the CAA has kept the FAA informed of 
the situation described above. The FAA has examined the findings of the 
CAA, 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. Therefore, we are proposing this AD, which 
would:
     Require repetitive application of DFL to LPC fan blade 
roots at more frequent intervals than the existing AD;
     Add the Trent 884B engine to the applicability;
     Add a fan blade P/N to the affected list of fan blades; 
and
     Relax the initial DFL repetitive application compliance 
time for certain fan blades that have never been removed from the disk.

Costs of Compliance

    There are approximately 388 RR RB211 Trent 875, 877, 884, 884B, 
892, 892B, and 895 series turbofan engines of the affected design in 
the worldwide fleet. We estimate that 106 engines installed on 
airplanes of U.S. registry would be affected by this proposed AD. We 
also estimate that it would take approximately six work hours per 
engine to perform the DFL application, and that the average labor rate 
is $65 per work hour. Based on these figures, we estimate the total 
cost of the proposed AD to U.S. operators to perform one repetitive 
application of DFL to the affected engines to be $41,340.

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 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. 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 summary of the costs to comply with this proposal and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2001-NE-12-AD'' in your request.

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 39-12761 (67 FR 
36803, May 28, 2002) and by adding a new airworthiness directive, to 
read as follows:

Rolls-Royce plc: Docket No. 2001-NE-12-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by April 19, 
2005.

Affected ADs

    (b) This AD supersedes AD 2002-10-15, Amendment 39-12761.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) RB211 Trent 875, 
877, 884, 884B, 892, 892B, and 895 series turbofan engines with low 
pressure compressor (LPC) fan blade part numbers (P/Ns): FK 30838, 
FK30840, FK30842, FW12960, FW12961, FW12962, FW13175, FW18548, or 
FW23552. These engines are installed on, but not limited to, Boeing 
777 series airplanes.

Unsafe Condition

    (d) This AD results from the discovery of dry film lubricant 
(DFL) condition appearing worse than anticipated on fan blades 
fitted to disks previously run for a significant period. This AD 
also results from the need to update the list of engine models 
affected, and to update the list of fan blade part numbers affected. 
The actions specified in this AD are intended to prevent LPC fan 
blade loss, which could result in an uncontained engine failure and 
possible aircraft damage.

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.
    (f) Apply an approved DFL to LPC fan blade roots as follows:
    (1) For LPC fan blades P/Ns FW13175, FW12960, FW12961, FW12962, 
FW18548, and FW23552 that have never been removed from the disk, 
apply DFL at the first removal from the disk or before 1,200 cycles-
in-service (CIS), whichever occurs first.
    (2) For LPC fan blades P/Ns FW13175, FW12960, FW12961, FW12962, 
FW18548, and FW23552 that have been removed from the disk since 
entering service, apply DFL before accumulating 600 cycles-since-new 
(CSN) or before accumulating 600 cycles-since-last DFL application, 
or within 200 CIS from the effective date of this AD, whichever 
occurs later.
    (3) For LPC fan blades P/Ns FK30842, FK30840, and FK300838, 
apply DFL before accumulating 600 CSN or before accumulating 600 
cycles-since-last DFL application, or within 100 CIS after July 2, 
2002 (effective date of superseded AD 2002-10-15), whichever occurs 
first.
    (4) Thereafter, reapply DFL to LPC fan blade roots within 600 
cycles-since-last DFL application.
    (5) Information on applying DFL to fan blade roots can be found 
in RR Alert Service Bulletin No. RB.211-72-AD347, Revision 6, dated 
April 22, 2004.

Alternative Methods of Compliance

    (g) 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.

[[Page 8305]]

Related Information

    (h) Civil Aviation Authority Airworthiness Directive G-2004-
0008, dated April 29, 2004, also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on February 10, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-3191 Filed 2-17-05; 8:45 am]
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