Airworthiness Directives; Rolls-Royce plc Models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 Turbofan Engines, 72310-72314 [E8-27298]
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
together with instructions for placing
the fuel system in a configuration used
to show compliance with that section.
(h) For each airplane showing
compliance with § 23.1353(g)(2) or
(g)(3), the operating procedures for
disconnecting the battery from its
charging source must be furnished.
(i) Information on the total quantity of
usable fuel for each fuel tank, and the
effect on the usable fuel quantity, as a
result of a failure of any pump, must be
furnished.
(j) Procedures for the safe operation of
the airplane’s systems and equipment,
both in normal use and in the event of
malfunction, must be furnished.
dwashington3 on PROD1PC60 with RULES
§ 23.1587
Performance information.
Instead of compliance with § 23.1587,
the following apply:
Unless otherwise prescribed,
performance information must be
provided over the altitude and
temperature ranges required by
§ 23.45(b).
(a) For all airplanes, the following
information must be furnished—
(1) The stalling speeds VSO and VS1
with the landing gear and wing flaps
retracted, determined at maximum
weight under § 23.49, and the effect on
these stalling speeds of angles of bank
up to 60 degrees;
(2) The steady rate and gradient of
climb with all engines operating,
determined under § 23.69(a);
(3) The landing distance, determined
under § 23.75 for each airport altitude
and standard temperature, and the type
of surface for which it is valid;
(4) The effect on landing distances of
operation on other than smooth hard
surfaces, when dry, determined under
§ 23.45(g); and
(5) The effect on landing distances of
runway slope and 50 percent of the
headwind component and 150 percent
of the tailwind component.
(b) Not applicable.
(c) Not applicable.
(d) In addition to paragraph (a) of this
section, the following information must
be furnished—
(1) The accelerate-stop distance
determined under § 23.55;
(2) The takeoff distance determined
under § 23.59(a);
(3) At the option of the applicant, the
takeoff run determined under § 23.59(b);
(4) The effect on accelerate-stop
distance, takeoff distance and, if
determined, takeoff run, of operation on
other than smooth hard surfaces, when
dry, determined under § 23.45(g);
(5) The effect on accelerate-stop
distance, takeoff distance, and if
determined, takeoff run, of runway
slope and 50 percent of the headwind
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14:57 Nov 26, 2008
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component and 150 percent of the
tailwind component;
(6) The net takeoff flight path
determined under § 23.61(b);
(7) The enroute gradient of climb/
descent with one engine inoperative,
determined under § 23.69(b);
(8) The effect, on the net takeoff flight
path and on the enroute gradient of
climb/descent with one engine
inoperative, of 50 percent of the
headwind component and 150 percent
of the tailwind component;
(9) Overweight landing performance
information (determined by
extrapolation and computed for the
range of weights between the maximum
landing and maximum takeoff weights)
as follows—
(i) The maximum weight for each
airport altitude and ambient
temperature at which the airplane
complies with the climb requirements of
§ 23.63(d)(2); and
(ii) The landing distance determined
under § 23.75 for each airport altitude
and standard temperature.
(10) The relationship between IAS
and CAS determined in accordance with
§ 23.1323(b) and (c).
(11) The altimeter system calibration
required by § 23.1325(e).
Issued in Kansas City, Missouri, on
November 18, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–28025 Filed 11–26–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23605; Directorate
Identifier 2005–NE–48–AD; Amendment 39–
15743; AD 2008–24–03]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc Models RB211 Trent 768–60, Trent
772–60, and Trent 772B–60 Turbofan
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
Rolls-Royce plc (RR) models RB211
Trent 768–60, Trent 772–60, and Trent
772B–60 turbofan engines that have not
incorporated RR Service Bulletin (SB)
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No. RB.211–72–E708, SB No. RB.211–
72–F227, or SB No. RB.211–72–E965, at
original issue or later revision. That AD
currently requires initial and repetitive
borescope inspections of the highpressure/intermediate-pressure (HP/IP)
turbine bearing internal oil vent tube,
scavenge tube, and tube heat shields for
wear and cracking, and removing tubes
from service if found with any cracks
beyond serviceable limits. That AD also
currently requires installation of a new
or modified HP/IP turbine bearings
support as terminating action for the
repetitive borescope inspections. This
AD has the same requirements, and
adds a repetitive inspection of the vent
flow restrictor for blockage. This AD
results from RR revising their alert
service bulletin for inspection of the
HP/IP turbine bearing internal oil vent
tube, scavenge tube, and tube heat
shields for damage, to include a
repetitive inspection of the vent flow
restrictor for blockage. We are issuing
this AD to prevent oil ejecting from the
HP/IP turbine bearings chamber and
igniting. Burning oil can cause the
intermediate-pressure (IP) shaft to
fracture, the IP turbine to overspeed,
and possible uncontained failure of the
engine.
DATES: Effective December 15, 2008. The
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of December 15, 2008.
We must receive any comments on
this AD by January 27, 2009.
ADDRESSES: Use one of the following
addresses to comment on this AD.
• Federal eRulemaking Portal: Go to
https://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, PO Box 31,
Derby, England, DE248BJ; telephone:
011–44–1332–242424; fax: 011–44–
1332–245418, for the service
information identified in this 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) 238–7175; fax (781)
238–7199.
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
On
February 24, 2006, the FAA issued AD
2006–05–03, Amendment 39–14500 (71
FR 11153, March 6, 2006). That AD
requires initial and repetitive borescope
inspections of the HP/IP turbine bearing
internal oil vent tube, scavenge tube,
and tube heat shields for wear and
cracking, and removing tubes from
service if found with any cracks beyond
serviceable limits. That AD also requires
installation of a new or modified HP/IP
turbine bearings support as terminating
action for the repetitive borescope
inspections. That AD was the result of
two reports of RR RB211 Trent 700
series engines found with the HP/IP
internal oil vent tube and scavenge tube
fretted by damaged heat shields on the
tubes. That condition, if not corrected,
could result in oil ejecting from the HP/
IP turbine bearings chamber and
igniting. Burning oil can cause the IP
shaft to fracture, the IP turbine to
overspeed, and possible uncontained
failure of the engine.
SUPPLEMENTARY INFORMATION:
dwashington3 on PROD1PC60 with RULES
Actions Since AD 2006–05–03 Was
Issued
Since AD 2006–05–03 was issued, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, notified us that they issued
EASA AD 2007–0255, dated September
14, 2007, to supersede EASA AD 2005–
0024, dated October 14, 2005. EASA AD
2007–0255 carries forward the
requirements from EASA AD 2005–
0024. EASA AD 2007–0255 adds
repetitive inspections of the vent flow
restrictor for blockage, based on RR
issuing Alert Service Bulletin (ASB) No.
RB.211–72–AE792, Revision 3. ASB
Revision 3, and now Revision 4, add
repetitive visual inspections of the vent
flow restrictor for blockage. This AD
requires the same actions as EASA AD
2007–0255.
Relevant Service Information
We have reviewed and approved the
technical contents of RR ASB No.
RB.211–72–AE792, Revision 4, dated
August 2, 2007. That ASB describes
procedures for initial and repetitive
borescope inspections of the HP/IP
turbine bearing internal oil vent tube,
scavenge tube, and tube heat shields for
wear and cracking, and removing tubes
from service if found with any cracks
beyond serviceable limits. That ASB
also describes procedures for
performing repetitive inspections of the
vent flow restrictor for blockage. That
ASB also references recently published
RR SB No. RB.211–72–F227 and RR SB
No. RB.211–72–E965 as terminating
actions for the inspection requirements.
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Bilateral Airworthiness Agreement
Comments Invited
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, the EASA has
kept the FAA 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.
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2006–23605; Directorate Identifier
2005–NE–48–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the rule that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
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 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).
FAA’s Determination and Requirements
of This AD
Although no airplanes that are
registered in the United States use these
RR RB211 Trent 768–60, Trent 772–60,
and Trent 772B–60 turbofan engines,
the possibility exists that the engines
could be used on airplanes that are
registered in the United States in the
future. The unsafe condition described
previously is likely to exist or develop
on other RR RB211 Trent 768–60, Trent
772–60, and Trent 772B–60 turbofan
engines of the same type design. We are
issuing this AD to prevent oil ejecting
from the HP/IP turbine bearings
chamber and igniting. Burning oil can
cause the IP shaft to fracture, the IP
turbine to overspeed, and possible
uncontained failure of the engine. This
AD requires:
• Initial and repetitive borescope
inspections of the HP/IP turbine bearing
internal oil vent tube, scavenge tube,
and tube heat shields for wear and
cracking; and
• Removing tubes from service if
found with any cracks beyond
serviceable limits; and
• Performing repetitive inspections of
the vent flow restrictor for blockage; and
• As terminating action to the
repetitive inspections required by the
AD, at the next 05 module overhaul, but
before May 31, 2010, removing the HP/
IP bearings support and replacing with
serviceable parts.
You must use the service information
described previously to perform the
inspections required by this AD.
FAA’s Determination of the Effective
Date
Since there are currently no domestic
operators of this engine model, notice
and opportunity for public comment
before issuing this AD are unnecessary.
Therefore, a situation exists that allows
the immediate adoption of this
regulation.
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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.
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
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
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 AD will
not have federalism implications under
Executive Order 13132. This AD will
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 this 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. Will 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 AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Under 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14500 71 FR
11153, March 6, 2006, and by adding a
new airworthiness directive,
Amendment 39–15743, to read as
follows:
■
2008–24–03 Rolls-Royce plc: Amendment
39–15743. Docket No. FAA–2006–23605;
Directorate Identifier 2005–NE–48–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 15, 2008.
Affected ADs
(b) This AD supersedes AD 2006–05–03,
Amendment 39–14500.
Applicability
(c) This AD applies to Rolls-Royce plc (RR)
models RB211 Trent 768–60, Trent 772–60,
and Trent 772B–60 turbofan engines that
have not incorporated RR Service Bulletin
(SB) No. RB.211–72–E708, SB No. RB.211–
72–F227, or SB No. RB.211–72–E965, at
original issue or later revision. These engines
are installed on, but not limited to, Airbus
A330–243, A330–341, A330–342, and A330–
343 airplanes.
Unsafe Condition
(d) This AD results from RR revising their
alert service bulletin for inspection of the
high-pressure/intermediate-pressure (HP/IP)
turbine bearing internal oil vent tube,
scavenge tube, and tube heat shields for
damage, to include a repetitive inspection of
the vent flow restrictor for blockage. We are
issuing this AD to prevent oil ejecting from
the HP/IP turbine bearings chamber and
igniting. Burning oil can cause the
intermediate-pressure (IP) shaft to fracture,
the IP turbine to overspeed, and possible
uncontained failure of the engine.
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.
On-Wing Initial Borescope Inspection
(f) Borescope inspect and assess the
condition of the HP/IP turbine support
assembly internal oil vent and scavenge tubes
and heat shields, using Section 3. of the
Accomplishment Instructions Part A, of RR
Alert Service Bulletin (ASB) No. RB.211–72–
AE792, Revision 4, dated August 2, 2007, and
Table 1 of this AD.
(g) The threshold life of the 05 module for
the initial borescope inspection is 10,000
operating hours since new or since overhaul,
or 2,500 cycles since new or since overhaul,
whichever occurs first.
TABLE 1—ON-WING BORESCOPE INSPECTION CRITERIA
For:
Action:
(1) 05 modules that exceed the threshold life on the effective date of
this AD:
(2) 05 modules that are below the threshold life on the effective date of
this AD:
Inspect within 1 month after the effective date of this AD.
Inspect by the threshold life or within 3 months from the effective date
of this AD, whichever occurs later.
On-Wing Repetitive Borescope Inspections
(h) Determine the serviceability and
establish the repetitive inspection intervals
using Table 2 of this AD.
TABLE 2—DETERMINATION OF SERVICEABILITY AND REPETITIVE INSPECTION INTERVAL
dwashington3 on PROD1PC60 with RULES
For:
Action:
(1) Outer heat shields of the vent or scavenge tube with no visible
damage:
(2) Outer heat shields of the vent or scavenge tube with partial cracking up to 90 degrees around the circumference or 10 mm along the
length of either outer heat shield:
(3) Outer heat shields of the vent or scavenge tube with partial cracking in excess of item (2) above, but less than 360 degrees around
the circumference of either outer heat shield:
(4) Outer heat shields of the vent or scavenge tube with cracking
around the complete circumference of either outer heat shield, or if
there is any missing material from either outer heat shield:
Re-inspect within intervals of 10,000 operating hours or 2,500 cycles,
whichever occurs first.
Re-inspect within intervals of 6,400 operating hours or 1,600 cycles,
whichever occurs first.
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Re-inspect within intervals of 1,600 operating hours or 400 cycles,
whichever occurs first.
Re-inspect or reject using Table 3 of this AD.
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
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TABLE 3—INSPECTION AND REJECTION CRITERIA FOR HEAT SHIELDS MEETING CONDITIONS IN ITEM (4) OF TABLE 2 OF
THIS AD
Condition:
Action:
(1) If the insulation blanket is in place inside the heat shield and preventing fretting between the heat shield and the tube.
(2) If either vent or scavenge tube has fretting at the outer heat shield
position where the maximum depth of fretting at any point around the
full 360 degrees of each tube is less than 0.46 mm (0.018 inch).
(3) If it is not possible to determine the maximum depth of fretting
around the full 360 degrees of each tube and item (1) above is not
applicable, then the HP/IP turbine support assembly must be rejected from service.
(4) If either vent or scavenge tube has fretting at the outer heat shield
position and the maximum depth of fretting is greater than 0.46 mm
(0.018 inch) then the HP/IP turbine support assembly must be rejected from service.
Inspect within intervals of 1,600 operating hours or 400 cycles, whichever occurs first.
Inspect within intervals of 400 operating hours or 100 cycles, whichever occurs first.
(i) For HP/IP turbine support assemblies
which have been previously inspected using
the superseded AD, or this AD:
(1) Re-inspect the internal oil vent and
scavenge tubes and heat shields before
exceeding the intervals established in Table
2 of this AD.
(2) Determine the serviceability and
intervals to the next inspection using Table
2 of this AD.
Inspections of the Vent Flow Restrictor After
On-Wing Borescope Inspection
(j) After a high-power ground run or not
later than 25 cycles after heat shield
inspection, inspect the vent flow restrictor,
Reject from service within 50 cycles of the inspection being carried out.
Reject within 10 cycles of the inspection being carried out.
using Section 3. of the Accomplishment
Instructions of RR SB No. RB.211–72–AE792,
Revision 4, dated August 2, 2007.
Repetitive Inspections of the Vent Flow
Restrictor After On-Wing Borescope
Inspection
(k) After each on-wing borescope
inspection, specified in paragraphs (f)
through (h) of this AD, repeat the inspection
of the vent flow restrictor, as specified in
paragraph (j) of this AD.
In-Shop Borescope Inspection
(l) For 05 modules in-shop which are not
undergoing strip and overhaul:
(1) Borescope inspect and assess the
condition of the HP/IP turbine support
assembly internal oil vent and scavenge tubes
and heat shields.
(2) Inspect the vent tubes and the vent flow
restrictor for carbon, after performing a highpower ground run.
(3) Use Section 3. of the Accomplishment
Instructions Part B, of RR ASB No. RB.211–
72–AE792, Revision 4, dated August 2, 2007,
and Table 4 of this AD to do the inspections.
(4) Determine the serviceability and
establish the interval to next inspection of
the HP/IP turbine support assembly internal
oil vent and scavenge tubes and heat shields,
using Table 4 of this AD:
TABLE 4—RE-INSPECTION CRITERIA
For:
Action:
(i) Outer heat shields of the vent and scavenge tubes with no visible
damage:
Re-inspect at a threshold of 10,000 operating hours time-since-new or
time-since-overhaul, or 2,500 cycles-since-new or cycles-since-overhaul, whichever occurs first.
Re-inspect at a not to exceed interval of 6,400 operating hours or
1,600 cycles, whichever occurs first.
(ii) Outer heat shields of the vent and scavenge tubes with cracking up
to 90 degrees around the circumference or 10 mm along the length
of either outer heat shield:
(iii) Outer heat shields of the vent and scavenge tubes with visible
cracking greater than 90 degrees of the circumference or 10 mm
along the length of either outer heat shield:
(m) For 05 modules in-shop which are
undergoing strip and overhaul, carry out the
terminating action specified in paragraph (n)
of this AD.
dwashington3 on PROD1PC60 with RULES
Terminating Action
(n) As terminating action to the repetitive
inspections required by this AD, at the next
05 module overhaul, but before May 31,
2010, remove the affected HP/IP bearings
supports and replace with serviceable parts.
Information on serviceable parts can be
found in RR SB No. RB.211–72–E708,
Revision 2, dated September 6, 2005, or in
RR SB No. RB.211–72–F227, Revision 1,
dated October 8, 2007, or in RR SB No.
RB.211–72–E965, Revision 1, dated October
4, 2005. To obtain these SBs, see paragraph
(r) of this AD for RR contact information.
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14:57 Nov 26, 2008
Jkt 217001
Reject the tube and perform the terminating action specified in paragraph (n) of this AD.
Definition
(o) For the purposes of this AD, serviceable
parts are new or reworked bearings supports
which reduce the adverse effects of HP3
cooling air turbulence on the HP/IP turbine
bearing internal oil vent and scavenge tubes
and tube heat shields, as described in RR SB
No. RB.211–72–E708, Revision 2, dated
September 6, 2005, or in RR SB No. RB.211–
72–F227, Revision 1, dated October 8, 2007,
or in RR SB No. RB.211–72–E965, Revision
1, dated October 4, 2005.
Alternative Methods of Compliance
(p) 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.
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Related Information
(q) European Aviation Safety Agency AD
2007–0255, dated September 14, 2007, also
addresses the subject of this AD.
Material Incorporated by Reference
(r) You must use the service information
specified in Table 5 of this AD to perform the
inspections required by this AD. The Director
of the Federal Register approved the
incorporation by reference of the documents
listed in Table 5 of this AD in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Rolls-Royce plc, PO Box 31, Derby,
England, DE248BJ; telephone: 011–44–1332–
242424; fax: 011–44–1332–245418, for a copy
of this service information. You may review
copies at the FAA, New England Region, 12
New England Executive Park, Burlington,
MA; or at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
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202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
TABLE 5—INCORPORATION BY REFERENCE
Rolls-Royce Alert Service Bulletin No.
Page
Revision
RB.211–72–AE792, including Appendix A .........................................................
Total Pages: 31
All .............................................
4
Issued in Burlington, Massachusetts, on
November 12, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–27298 Filed 11–26–08; 8:45 am]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1020 Directorate
Identifier 2008–CE–053–AD; Amendment
39–15751; AD 2008–24–11]
RIN 2120–AA64
Airworthiness Directives; Vulcanair
S.p.A. Model P68 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
dwashington3 on PROD1PC60 with RULES
The Safe Fatigue Limits (SFL) of the Wing
Structure in the P68 Series aircraft have been
redefined from the current 8,500 Flight Hours
to a new value to be calculated up to a
maximum of 17,500 Flight Hours. This has
been developed by Vulcanair under Change
No. MOD.P68/79 Rev. 1 and approved by
EASA with No. EASA.A.C.02482 on 07 June
2006.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
January 2, 2009.
On January 2, 2009, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
14:57 Nov 26, 2008
Jkt 217001
August 2, 2007.
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sarjapur Nagarajan, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4145; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a Note within the AD.
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on September 26, 2008 (73 FR
55786). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
BILLING CODE 4910–13–P
VerDate Aug<31>2005
Date
Costs of Compliance
Based on the service information, we
estimate that this AD will affect 72
products of U.S. registry. We also
estimate that it will take about 80 workhours per product to comply with basic
requirements of this AD. The average
labor rate is $80 per work-hour.
Based on these figures, we estimate
the cost of this AD to the U.S. operators
to be $460,800, or $6,400 per product.
We have no way of determining the
number of products that may need any
necessary follow-on actions.
The Safe Fatigue Limits (SFL) of the Wing
Structure in the P68 Series aircraft have been
redefined from the current 8,500 Flight Hours
to a new value to be calculated up to a
maximum of 17,500 Flight Hours. This has
been developed by Vulcanair under Change
No. MOD.P68/79 Rev. 1 and approved by
EASA with No. EASA.A.C.02482 on 07 June
2006.
The new Safe Fatigue Limits depend on:
(a) Status of the modification
(reinforcement) of the wing structure itself
(Partenavia Service Bulletin No. 65 refers);
and
(b) Aircraft Flight Hours accumulated
before the modification (reinforcement) was
implemented.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
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.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
PO 00000
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]]>Agencies
[Federal Register Volume 73, Number 230 (Friday, November 28, 2008)]
[Rules and Regulations]
[Pages 72310-72314]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-27298]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23605; Directorate Identifier 2005-NE-48-AD;
Amendment 39-15743; AD 2008-24-03]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc Models RB211 Trent 768-
60, Trent 772-60, and Trent 772B-60 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Rolls-Royce plc (RR) models RB211 Trent 768-60, Trent 772-60,
and Trent 772B-60 turbofan engines that have not incorporated RR
Service Bulletin (SB) No. RB.211-72-E708, SB No. RB.211-72-F227, or SB
No. RB.211-72-E965, at original issue or later revision. That AD
currently requires initial and repetitive borescope inspections of the
high-pressure/intermediate-pressure (HP/IP) turbine bearing internal
oil vent tube, scavenge tube, and tube heat shields for wear and
cracking, and removing tubes from service if found with any cracks
beyond serviceable limits. That AD also currently requires installation
of a new or modified HP/IP turbine bearings support as terminating
action for the repetitive borescope inspections. This AD has the same
requirements, and adds a repetitive inspection of the vent flow
restrictor for blockage. This AD results from RR revising their alert
service bulletin for inspection of the HP/IP turbine bearing internal
oil vent tube, scavenge tube, and tube heat shields for damage, to
include a repetitive inspection of the vent flow restrictor for
blockage. We are issuing this AD to prevent oil ejecting from the HP/IP
turbine bearings chamber and igniting. Burning oil can cause the
intermediate-pressure (IP) shaft to fracture, the IP turbine to
overspeed, and possible uncontained failure of the engine.
DATES: Effective December 15, 2008. The Director of the Federal
Register approved the incorporation by reference of certain
publications listed in the regulations as of December 15, 2008.
We must receive any comments on this AD by January 27, 2009.
ADDRESSES: Use one of the following addresses to comment on this AD.
Federal eRulemaking Portal: Go to https://
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, PO Box 31, Derby, England, DE248BJ;
telephone: 011-44-1332-242424; fax: 011-44-1332-245418, for the service
information identified in this 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) 238-7175; fax (781) 238-7199.
[[Page 72311]]
SUPPLEMENTARY INFORMATION: On February 24, 2006, the FAA issued AD
2006-05-03, Amendment 39-14500 (71 FR 11153, March 6, 2006). That AD
requires initial and repetitive borescope inspections of the HP/IP
turbine bearing internal oil vent tube, scavenge tube, and tube heat
shields for wear and cracking, and removing tubes from service if found
with any cracks beyond serviceable limits. That AD also requires
installation of a new or modified HP/IP turbine bearings support as
terminating action for the repetitive borescope inspections. That AD
was the result of two reports of RR RB211 Trent 700 series engines
found with the HP/IP internal oil vent tube and scavenge tube fretted
by damaged heat shields on the tubes. That condition, if not corrected,
could result in oil ejecting from the HP/IP turbine bearings chamber
and igniting. Burning oil can cause the IP shaft to fracture, the IP
turbine to overspeed, and possible uncontained failure of the engine.
Actions Since AD 2006-05-03 Was Issued
Since AD 2006-05-03 was issued, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, notified us that they issued EASA AD 2007-0255,
dated September 14, 2007, to supersede EASA AD 2005-0024, dated October
14, 2005. EASA AD 2007-0255 carries forward the requirements from EASA
AD 2005-0024. EASA AD 2007-0255 adds repetitive inspections of the vent
flow restrictor for blockage, based on RR issuing Alert Service
Bulletin (ASB) No. RB.211-72-AE792, Revision 3. ASB Revision 3, and now
Revision 4, add repetitive visual inspections of the vent flow
restrictor for blockage. This AD requires the same actions as EASA AD
2007-0255.
Relevant Service Information
We have reviewed and approved the technical contents of RR ASB No.
RB.211-72-AE792, Revision 4, dated August 2, 2007. That ASB describes
procedures for initial and repetitive borescope inspections of the HP/
IP turbine bearing internal oil vent tube, scavenge tube, and tube heat
shields for wear and cracking, and removing tubes from service if found
with any cracks beyond serviceable limits. That ASB also describes
procedures for performing repetitive inspections of the vent flow
restrictor for blockage. That ASB also references recently published RR
SB No. RB.211-72-F227 and RR SB No. RB.211-72-E965 as terminating
actions for the inspection requirements.
Bilateral Airworthiness Agreement
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, the EASA has kept the FAA 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 This AD
Although no airplanes that are registered in the United States use
these RR RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan
engines, the possibility exists that the engines could be used on
airplanes that are registered in the United States in the future. The
unsafe condition described previously is likely to exist or develop on
other RR RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan
engines of the same type design. We are issuing this AD to prevent oil
ejecting from the HP/IP turbine bearings chamber and igniting. Burning
oil can cause the IP shaft to fracture, the IP turbine to overspeed,
and possible uncontained failure of the engine. This AD requires:
Initial and repetitive borescope inspections of the HP/IP
turbine bearing internal oil vent tube, scavenge tube, and tube heat
shields for wear and cracking; and
Removing tubes from service if found with any cracks
beyond serviceable limits; and
Performing repetitive inspections of the vent flow
restrictor for blockage; and
As terminating action to the repetitive inspections
required by the AD, at the next 05 module overhaul, but before May 31,
2010, removing the HP/IP bearings support and replacing with
serviceable parts.
You must use the service information described previously to
perform the inspections required by this AD.
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this engine
model, notice and opportunity for public comment before issuing this AD
are unnecessary. Therefore, a situation exists that allows the
immediate adoption of this regulation.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2006-23605;
Directorate Identifier 2005-NE-48-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
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 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 https://
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.
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
[[Page 72312]]
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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this 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. Will 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 AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Under 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
0
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]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-14500 71 FR
11153, March 6, 2006, and by adding a new airworthiness directive,
Amendment 39-15743, to read as follows:
2008-24-03 Rolls-Royce plc: Amendment 39-15743. Docket No. FAA-2006-
23605; Directorate Identifier 2005-NE-48-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
15, 2008.
Affected ADs
(b) This AD supersedes AD 2006-05-03, Amendment 39-14500.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) models RB211 Trent
768-60, Trent 772-60, and Trent 772B-60 turbofan engines that have
not incorporated RR Service Bulletin (SB) No. RB.211-72-E708, SB No.
RB.211-72-F227, or SB No. RB.211-72-E965, at original issue or later
revision. These engines are installed on, but not limited to, Airbus
A330-243, A330-341, A330-342, and A330-343 airplanes.
Unsafe Condition
(d) This AD results from RR revising their alert service
bulletin for inspection of the high-pressure/intermediate-pressure
(HP/IP) turbine bearing internal oil vent tube, scavenge tube, and
tube heat shields for damage, to include a repetitive inspection of
the vent flow restrictor for blockage. We are issuing this AD to
prevent oil ejecting from the HP/IP turbine bearings chamber and
igniting. Burning oil can cause the intermediate-pressure (IP) shaft
to fracture, the IP turbine to overspeed, and possible uncontained
failure of the engine.
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.
On-Wing Initial Borescope Inspection
(f) Borescope inspect and assess the condition of the HP/IP
turbine support assembly internal oil vent and scavenge tubes and
heat shields, using Section 3. of the Accomplishment Instructions
Part A, of RR Alert Service Bulletin (ASB) No. RB.211-72-AE792,
Revision 4, dated August 2, 2007, and Table 1 of this AD.
(g) The threshold life of the 05 module for the initial
borescope inspection is 10,000 operating hours since new or since
overhaul, or 2,500 cycles since new or since overhaul, whichever
occurs first.
Table 1--On-Wing Borescope Inspection Criteria
------------------------------------------------------------------------
For: Action:
------------------------------------------------------------------------
(1) 05 modules that exceed the threshold Inspect within 1 month after
life on the effective date of this AD: the effective date of this
AD.
(2) 05 modules that are below the Inspect by the threshold
threshold life on the effective date of life or within 3 months
this AD: from the effective date of
this AD, whichever occurs
later.
------------------------------------------------------------------------
On-Wing Repetitive Borescope Inspections
(h) Determine the serviceability and establish the repetitive
inspection intervals using Table 2 of this AD.
Table 2--Determination of Serviceability and Repetitive Inspection
Interval
------------------------------------------------------------------------
For: Action:
------------------------------------------------------------------------
(1) Outer heat shields of the vent or Re-inspect within intervals
scavenge tube with no visible damage: of 10,000 operating hours
or 2,500 cycles, whichever
occurs first.
(2) Outer heat shields of the vent or Re-inspect within intervals
scavenge tube with partial cracking up to of 6,400 operating hours or
90 degrees around the circumference or 10 1,600 cycles, whichever
mm along the length of either outer heat occurs first.
shield:
(3) Outer heat shields of the vent or Re-inspect within intervals
scavenge tube with partial cracking in of 1,600 operating hours or
excess of item (2) above, but less than 400 cycles, whichever
360 degrees around the circumference of occurs first.
either outer heat shield:
(4) Outer heat shields of the vent or Re-inspect or reject using
scavenge tube with cracking around the Table 3 of this AD.
complete circumference of either outer
heat shield, or if there is any missing
material from either outer heat shield:
------------------------------------------------------------------------
[[Page 72313]]
Table 3--Inspection and Rejection Criteria for Heat Shields Meeting
Conditions in Item (4) of Table 2 of This AD
------------------------------------------------------------------------
Condition: Action:
------------------------------------------------------------------------
(1) If the insulation blanket is in place Inspect within intervals of
inside the heat shield and preventing 1,600 operating hours or
fretting between the heat shield and the 400 cycles, whichever
tube. occurs first.
(2) If either vent or scavenge tube has Inspect within intervals of
fretting at the outer heat shield 400 operating hours or 100
position where the maximum depth of cycles, whichever occurs
fretting at any point around the full 360 first.
degrees of each tube is less than 0.46 mm
(0.018 inch).
(3) If it is not possible to determine the Reject from service within
maximum depth of fretting around the full 50 cycles of the inspection
360 degrees of each tube and item (1) being carried out.
above is not applicable, then the HP/IP
turbine support assembly must be rejected
from service.
(4) If either vent or scavenge tube has Reject within 10 cycles of
fretting at the outer heat shield the inspection being
position and the maximum depth of carried out.
fretting is greater than 0.46 mm (0.018
inch) then the HP/IP turbine support
assembly must be rejected from service.
------------------------------------------------------------------------
(i) For HP/IP turbine support assemblies which have been
previously inspected using the superseded AD, or this AD:
(1) Re-inspect the internal oil vent and scavenge tubes and heat
shields before exceeding the intervals established in Table 2 of
this AD.
(2) Determine the serviceability and intervals to the next
inspection using Table 2 of this AD.
Inspections of the Vent Flow Restrictor After On-Wing Borescope
Inspection
(j) After a high-power ground run or not later than 25 cycles
after heat shield inspection, inspect the vent flow restrictor,
using Section 3. of the Accomplishment Instructions of RR SB No.
RB.211-72-AE792, Revision 4, dated August 2, 2007.
Repetitive Inspections of the Vent Flow Restrictor After On-Wing
Borescope Inspection
(k) After each on-wing borescope inspection, specified in
paragraphs (f) through (h) of this AD, repeat the inspection of the
vent flow restrictor, as specified in paragraph (j) of this AD.
In-Shop Borescope Inspection
(l) For 05 modules in-shop which are not undergoing strip and
overhaul:
(1) Borescope inspect and assess the condition of the HP/IP
turbine support assembly internal oil vent and scavenge tubes and
heat shields.
(2) Inspect the vent tubes and the vent flow restrictor for
carbon, after performing a high-power ground run.
(3) Use Section 3. of the Accomplishment Instructions Part B, of
RR ASB No. RB.211-72-AE792, Revision 4, dated August 2, 2007, and
Table 4 of this AD to do the inspections.
(4) Determine the serviceability and establish the interval to
next inspection of the HP/IP turbine support assembly internal oil
vent and scavenge tubes and heat shields, using Table 4 of this AD:
Table 4--Re-Inspection Criteria
------------------------------------------------------------------------
For: Action:
------------------------------------------------------------------------
(i) Outer heat shields of the vent and Re-inspect at a threshold of
scavenge tubes with no visible damage: 10,000 operating hours time-
since-new or time-since-
overhaul, or 2,500 cycles-
since-new or cycles-since-
overhaul, whichever occurs
first.
(ii) Outer heat shields of the vent and Re-inspect at a not to
scavenge tubes with cracking up to 90 exceed interval of 6,400
degrees around the circumference or 10 mm operating hours or 1,600
along the length of either outer heat cycles, whichever occurs
shield: first.
(iii) Outer heat shields of the vent and Reject the tube and perform
scavenge tubes with visible cracking the terminating action
greater than 90 degrees of the specified in paragraph (n)
circumference or 10 mm along the length of this AD.
of either outer heat shield:
------------------------------------------------------------------------
(m) For 05 modules in-shop which are undergoing strip and
overhaul, carry out the terminating action specified in paragraph
(n) of this AD.
Terminating Action
(n) As terminating action to the repetitive inspections required
by this AD, at the next 05 module overhaul, but before May 31, 2010,
remove the affected HP/IP bearings supports and replace with
serviceable parts. Information on serviceable parts can be found in
RR SB No. RB.211-72-E708, Revision 2, dated September 6, 2005, or in
RR SB No. RB.211-72-F227, Revision 1, dated October 8, 2007, or in
RR SB No. RB.211-72-E965, Revision 1, dated October 4, 2005. To
obtain these SBs, see paragraph (r) of this AD for RR contact
information.
Definition
(o) For the purposes of this AD, serviceable parts are new or
reworked bearings supports which reduce the adverse effects of HP3
cooling air turbulence on the HP/IP turbine bearing internal oil
vent and scavenge tubes and tube heat shields, as described in RR SB
No. RB.211-72-E708, Revision 2, dated September 6, 2005, or in RR SB
No. RB.211-72-F227, Revision 1, dated October 8, 2007, or in RR SB
No. RB.211-72-E965, Revision 1, dated October 4, 2005.
Alternative Methods of Compliance
(p) 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
(q) European Aviation Safety Agency AD 2007-0255, dated
September 14, 2007, also addresses the subject of this AD.
Material Incorporated by Reference
(r) You must use the service information specified in Table 5 of
this AD to perform the inspections required by this AD. The Director
of the Federal Register approved the incorporation by reference of
the documents listed in Table 5 of this AD in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-Royce plc, PO Box 31,
Derby, England, DE248BJ; telephone: 011-44-1332-242424; fax: 011-44-
1332-245418, for a copy of this service information. You may review
copies at the FAA, New England Region, 12 New England Executive
Park, Burlington, MA; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call
[[Page 72314]]
202-741-6030, or go to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Table 5--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Rolls-Royce Alert Service Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
RB.211-72-AE792, including Appendix A.. All...................... 4 August 2, 2007.
Total Pages: 31
----------------------------------------------------------------------------------------------------------------
Issued in Burlington, Massachusetts, on November 12, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-27298 Filed 11-26-08; 8:45 am]
BILLING CODE 4910-13-P
