[Federal Register Volume 62, Number 83 (Wednesday, April 30, 1997)]
[Rules and Regulations]
[Pages 23339-23341]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-10469]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-09; Amendment 39-9970; AD 97-06-13]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB.211 Trent 800 Series
Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Rolls-Royce plc RB.211 Trent 800 series turbofan
engines. This action requires initial and repetitive visual and
fluorescent penetrant inspections (FPI) of the angled drive upper
shroud tube for frettage and cracking, initial and repetitive visual
inspections and FPI for cracking, a one-tine FPI for porosity of the
intermediate gearbox housing (IGH), and initial and repetitive visual
inspections for cracking of the external gearbox lower bevel box (LBB)
housing. In addition, this action requires initial and repetitive
master magnetic chip detector inspections. Finally, prior to initiation
of Extended Range Twin-Engine Operations (ETOPS), or prior to September
30, 1997, whichever occurs first, this action requires installation of
a redesigned angled drive upper shroud tube and a lower splitter
fairing with revised sealing. This amendment is prompted by reports of
loss of oil from the angle drive upper shroud tube, the IGH, the LBB,
and by reports of bearing failures. The actions specified by this AD
are intended to prevent loss of oil, which could cause an engine fire.
This AD is also intended to prevent inflight engine shutdowns and
airplane diversions caused by oil loss and from bearing failures.
DATES: Effective May 15, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 15, 1997.
Comments for inclusion in the Rules Docket must be received on or
before June 30, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 97-ANE-09, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``9__ad
__engineprop@faa.dot.gov''. Comments sent via the Internet must contain
the docket number in the subject line.
The service information referenced in this AD may be obtained from
Rolls-Royce North America, Inc., 2001 South Tibbs Ave., Indianapolis,
IN 46241; telephone (317) 230-3995, fax (317) 230-4743. This
information may be examined at the FAA, New England Region, Office of
the Assistant Chief Counsel, 12 New England Executive Park, Burlington,
MA; or at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Chris Gavriel, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (617)
238-7147, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: The Civil Aviation Authority, which is
the airworthiness authority for the United Kingdom (UK), recently
notified the FAA that an unsafe condition may exist on Rolls-Royce
plc RB.211 Trent 800 series turbofan engines. The CAA advises that
they have received ten reports of loss of oil and one report of
intermediate pressure compressor (IPC) front bearing roller
retainer tang failure.
Loss of oil: The reports to the CAA indicate that oil can leak from
the angled drive upper shroud tube, from the intermediate gearbox
housing (IGH), or from the external gearbox lower bevel box (LBB)
housing. The angled drive upper shroud tube may contact adjacent lower
bifurcation structure initiating frettage on the tube. The nacelle
structure may also transfer vibratory loads onto the tube to the point
of fracture, causing oil leakage. The IGH, which is attached to the
angled drive upper shroud tube assembly, or the LBB, which is attached
to the external gearbox, can develop cracks, causing oil leakage.
Bearing failure: The reports to the CAA indicate that the IPC front
bearing, and bearings in the IGH and internal gearbox can fail and
cause an inflight shutdown and aircraft diversion.
These conditions, if not corrected, can result in loss of oil, that
could cause an engine fire. These conditions may also result in
inflight engine shutdowns and airplane diversions caused by oil loss
and from bearing failures.
Rolls-Royce plc has issued the following service documents:
Mandatory Service Bulletin (SB) No. RB.211-72-C089, Revision 1, dated
January 24, 1997, that describes procedures for inspection of angled
drive upper shroud tubes for frettage and cracks; Mandatory SB No.
RB.211-72-C129, Revision 2, dated March 21, 1997, that describes
procedures for inspection of the IGH for cracks and porosity and the
LBB housing for cracks; SB No. RB.211-72-C114, Original, dated February
6, 1997, that describes procedures for installation of an improved
angled drive upper shroud tube with a lower splitter fairing with
revised sealing; and Mandatory SB No.
[[Page 23340]]
RB.211-79-C093, Revision 1, dated February 28, 1997, that describes
procedures for inspection of the master magnetic chip detector. The CAA
classified three of these service documents, identified above, as
mandatory in order to assure the airworthiness of these engines.
This engine model is manufactured in the UK and is type
certificated for operation in the United States (US) 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 US.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of the same type design registered in
the US, the proposed AD would require: initial and repetitive visual
and FPI of the angled drive upper shroud tube for frettage and
cracking, initial and repetitive visual inspections and FPI of the IGH
for cracking, a one-time FPI of the IGH for porosity, and initial and
repetitive visual inspections of the LBB housing for cracking. In
addition, this action requires initial and repetitive master magnetic
chip detector inspections. Finally, prior to initiation of Extended
Range Twin-Engine Operations (ETOPS), or prior to September 30, 1997,
whichever occurs first, this action requires installation of an
improved angled drive upper shroud tube with a lower splitter fairing
with revised sealing. The actions would be required to be accomplished
in accordance with the service documents described previously.
Following identification of additional corrective actions that would
negate the need to continue frequent inspections, additional rulemaking
may be forthcoming.
Additionally, since this AD affects ETOPS service, the requirement
to install the improved angled drive upper shroud tube with a lower
splitter fairing with revised sealing prior to entering ETOPS service
is in accordance with the airplane ETOPS requirements and has been
coordinated with and concurred by the Transport Airplane Directorate of
the FAA.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-ANE-09.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, may
be obtained from the Rules Docket at the location provided under the
caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 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 adding the following new
airworthiness directive:
97-06-13 Rolls-Royce plc: Amendment 39-9970. Docket 97-ANE-09.
Applicability: Rolls-Royce plc (R-R) RB.211 Trent 800 series
turbofan engines, installed on but not limited to Boeing 777 series
aircraft.
Note 1: This airworthiness directive (AD) applies to each engine
identified in the preceding applicability provision, regardless of
whether it has been modified, altered, or repaired in the area
subject to the requirements of this AD. For engines that have been
modified, altered, or repaired so that the performance of the
requirements of this AD is affected, the owner/operator must request
approval for an alternative method of compliance in accordance with
paragraph (d) of this AD. The request should include an assessment
of the effect of the modification, alteration, or repair on the
unsafe condition addressed by this AD; and, if the unsafe condition
has not been eliminated, the request should include specific
proposed actions to address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of oil, that could cause an engine fire, and
inflight engine shutdowns and airplane diversions caused by oil loss
and from bearing failures, accomplish the following:
(a) Inspect angle drive upper shroud tubes as follows:
(1) Within 50 CIS after the effective date of this AD, visually
inspect and measure the frettage and fluorescent penetrant inspect
[[Page 23341]]
(FPI) for cracks the angle drive upper shroud tubes in accordance
with R-R Service SB No. RB.211-72-C089, Revision 1, dated January
24, 1997.
(2) Thereafter, at intervals not to exceed 50 CIS since last
inspection, visually inspect and measure the frettage and FPI for
cracks the angled drive upper shroud tubes, in accordance with R-R
SB No. RB.211-72-C089, Revision 1, dated January 24, 1997.
(3) Prior to further flight, remove from service angled drive
upper shroud tubes that exhibit frettage measured in excess of 0.020
inches, or any cracks, and replace with serviceable parts.
(4) Installation of an improved angled drive upper shroud tube
with a lower splitter fairing with revised sealing in accordance
with R-R SB No. RB.211-72-C114, dated February 6, 1997, constitutes
terminating action to the inspection requirements of paragraphs
(a)(1), (a)(2), and (a)(3) of this AD.
(5) Prior to initiation of ETOPS, or prior to September 30,
1997, whichever occurs first, install an improved angled drive upper
shroud tube with a lower splitter fairing with revised sealing in
accordance with R-R SB No. RB.211-72-C114, dated February 6, 1997.
(b) Inspect the intermediate gearbox housing (IGH) and external
gearbox lower bevel box (LBB) housing as follows:
(1) Within 5 CIS after the effective date of this AD, perform an
initial visual inspection of the IGH and LBB housing for cracks, in
accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2,
dated March 21, 1997.
(2) Within 10 CIS after the effective date of this AD, perform
an initial FPI of the IGH for cracks, in accordance with R-R
Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997.
(3) Thereafter, at intervals not to exceed 5 CIS since last
visual inspection, visually inspect the IGH and LBB housing for
cracks, and at intervals not to exceed 10 CIS since last FPI, FPI
the IGH, in accordance with R-R Mandatory SB No. RB.211-72-C129,
Revision 2, dated March 21, 1997.
(4) Within 10 CIS after the effective date of this AD, perform
an FPI of the IGH for porosity in accordance with R-R Mandatory SB
No. RB.211-72-C129, Revision 2, dated March 21, 1997.
(5) Within the next 5 CIS, remove from service IGHs that exhibit
porosity levels in excess of the acceptable criteria listed in the
SB and replace with serviceable parts.
(6) Prior to further flight, remove from service cracked IGHs
and LLB housings and replace with serviceable parts.
(c) Inspect the master magnetic chip detector as follows:
(1) Within 100 hours time in service (TIS) after the effective
date of this AD, perform an initial inspection of the master
magnetic chip detector in accordance with Mandatory SB No. RB.211-
79-C093, Revision 1, February 28, 1997.
(2) Thereafter, at intervals not less than 60 hours TIS and not
greater than 130 hours TIS since last inspection, perform repetitive
inspections of the master magnetic chip detector in accordance with
Mandatory SB No. RB.211-79-C093, Revision 1, dated February 28,
1997.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Engine Certification Office. The
request should be forwarded through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Engine Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(e) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the aircraft to a location where
the inspection requirements of this AD can be accomplished.
(f) The actions required by this AD shall be performed in
accordance with the following R-R service documents:
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Document No. Pages Revision Date
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SB No. RB.211-72-C089.................... 1-3 1........................ Jan. 24, 1997.
Total pages: 3.
SB No. RB.211-72-C129.................... 1-3 2........................ Mar. 21, 1997.
4-6 1........................ Mar. 7, 1997.
7 2........................ Mar. 21, 1997.
Total pages: 7.
SB No. RB.211-72-C114.................... 1-48 Original................. Feb. 6, 1997.
Supplement............................... 1-4 Original................. Feb. 6, 1997.
Total pages: 52.
SB No. RB.211-79-C093.................... 1,2 1........................ Feb. 28, 1997.
Total pages: 2.
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This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from Rolls-Royce North America,
Inc., 2001 South Tibbs Ave., Indianapolis, IN 46241; telephone (317)
230-3995, fax (317) 230-4743. Copies may be inspected at the FAA,
New England Region, Office of the Assistant Chief Counsel, 12 New
England Executive Park, Burlington, MA; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(g) This amendment becomes effective on May 15, 1997.
Issued in Burlington, Massachusetts, on April 14, 1997.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 97-10469 Filed 4-29-97; 8:45 am]
BILLING CODE 4910-13-U
