[Federal Register: June 25, 2003 (Volume 68, Number 122)]
[Rules and Regulations]
[Page 37735-37738]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25jn03-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NE-13-AD; Amendment 39-13200; AD 2003-12-15]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce RB211 Series Turbofan
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD), that
is applicable to Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37,
and RB211-535E4-B-75 series turbofan engines. This amendment requires
introducing an alternative technique to ultrasonically inspect
installed fan blades on-wing using a surface wave
[[Page 37736]]
ultrasonic probe. This action also adds the application of Metco 58
blade root coating as an optional terminating action. This amendment is
prompted by the discovery of cracks on LPC fan blade roots during an
engine overhaul. The actions specified by this AD are intended to
detect cracks in LPC fan blade roots, which if not detected, could lead
to uncontained multiple fan blade failure, and damage to the airplane.
DATES: Effective July 30, 2003. The incorporation by reference of
certain publications listed in the regulations is approved by the
Director of the Federal Register as of July 30, 2003.
ADDRESSES: The service information referenced in this AD may be
obtained from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ;
telephone: 011-44-1332-242-424; fax: 011-44-1332-249-936. This
information may be examined, by appointment, at the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
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: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone: (781)
238-7176; fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that is
applicable to Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37,
and RB211-535E4-B-75 series turbofan engines was published in the
Federal Register on August 9, 2001 (66 FR 41808). That proposal was
revised by a supplemental notice of proposed rulemaking (SNPRM) to
amend part 39 of the Federal Aviation Regulations (14 CFR part 39).
That SNPRM was published in the Federal Register on February 20, 2003
(68 FR 8157). That action proposed to introduce an alternative
technique to ultrasonically inspect installed fan blades on-wing using
a surface wave ultrasonic probe and also to add the application of
Metco 58 blade root coating as an optional terminating action in
accordance with Rolls-Royce plc mandatory service bulletin RB.211-72-
C879, Revision 3, dated October 9, 2002.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. The FAA
has determined that air safety and the public interest require the
adoption of the rule as proposed.
Regulatory Analysis
This final rule does not have federalism implications, as defined
in Executive Order 13132, because it 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. Accordingly,
the FAA has not consulted with state authorities prior to publication
of this final rule.
For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
by contacting 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
0
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
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. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2003-12-15 Rolls-Royce plc: Amendment 39-13200. Docket No. 2000-NE-
13-AD.
Applicability: This airworthiness directive (AD) is applicable
to Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and RB211-
535E4-B-75 series turbofan engines with low pressure compressor
(LPC) fan blades with the part numbers (P/Ns) listed in Table 1 of
this AD. These engines are installed on, but not limited to Boeing
757 and Tupolev Tu204 series airplanes. Table 1 follows:
Table 1.--Applicable LPC Fan Blade P/Ns
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UL16135 UL16171 UL16182 UL19643 UL20044
UL20132 UL20616 UL21345 UL22286 UL23122
UL24525 UL24528 UL24530 UL24532 UL24534
UL27992 UL28601 UL28602 UL29511 UL29556
UL30817 UL30819 UL30933 UL30935 UL33707
UL33709 UL36992 UL37090 UL37272 UL37274
UL37276 UL37278 UL38029 UL38032
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Note 1: This 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 (g) 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: Compliance with this AD is required as indicated,
unless already done.
To detect cracks in LPC fan blade roots, which if not detected,
could lead to uncontained multiple fan blade failure, and damage to
the airplane, do the following:
(a) If you have a full set of fan blades, modified using RR
service bulletin RB.211-72-C946, dated August 6, 2002, that can be
identified by a blue triangle etched on the blade airfoil suction
surface close to the leading edge tip of each blade, no further
action is required.
(b) On RB211-535E4 engines, operated to Flight Profile A,
ultrasonically inspect, and if
[[Page 37737]]
required, relubricate using the following Table 2:
Table 2.--RB211-535E4 Flight Profile A
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Initial Repeat
inspection inspection
Engine location within Type action In accordance with within
(CSN) (CSN)
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(1) On-wing..................... 17,350 (i) Root Probe, inspect RB.211-72-C879 Revision 1,400.
and relubricate, OR. 3, 3.A.(1) through
3.A.(7), dated October
9, 2002.
(ii) Wave Probe......... RB.211-72-C879 Revision 1,150.
3, 3.B.(1) through
3.B.(7), dated October
9, 2002.
---------------------------------
(2) In Shop..................... 17,350 Root Probe, inspect and RB.211-72-C879 Revision 1,400.
relubricate. 3, 3.C.(1) through
3.C.(4), dated October
9, 2002.
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(c) On RB211-535E4 engines, operated to Flight Profile B,
ultrasonically inspect, and if required, relubricate using the
following Table 3:
Table 3.--RB211-535E4 Flight Profile B
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Initial Repeat
inspection inspection
Engine location within Type action In accordance with within
(CSN) (CSN)
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(1) On-wing..................... 12,350 (i) Root Probe, inspect RB.211-72-C879 Revision 850.
and relubricate, OR. 3, 3.A.(1) through
3.A.(7), dated October
9, 2002.
(ii) Wave Probe......... RB.211-72-C879 Revision 700.
3, 3.B.(1) through
3.B.(7), dated October
9, 2002.
---------------------------------
(2) In Shop..................... 12,350 Root Probe, inspect and RB.211-72-C879 Revision 850.
relubricate. 3, 3.C.(1) through
3.C.(4), dated October
9, 2002.
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(d) On RB211-535E4 engines, operated to combined Flight Profile
A and B, ultrasonically inspect, and if required, relubricate using
the following Table 4:
Table 4.--RB211-535E4 Flight Profile A and B
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Initial inspection
Engine location within (CSN) Type action In accordance with Repeat inspection within (CSN)
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(1) On-wing..................... 65% hard life (To (i) Root Probe, inspect RB.211-72-C879 Revision As current flight profile.
calculate, see and relubricate, OR. 3, 3.A.(1) through
Compliance Section 3.A.(7), dated October
1.C.(4)). 9, 2002.
(ii) Wave Probe........ RB.211-72-C879 Revision As current flight profile.
3, 3.B.(1) through
3.B.(7), dated October
9, 2002.
---------------------------------
(2) In Shop..................... 65% hard life (To Root Probe, inspect and RB.211-72-C879 Revision As current flight profile.
calculate, see relubricate. 3, 3.C.(1) through
Compliance Section 3.C.(4), dated October
1.C.(4)). 9, 2002.
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Note 2: Fan blades that have been operated within RB211-535E4
Flight Profile A and B will have final life as defined in the Time
Limits Manual. See References Section 1.G.(3), of MSB RB.211-72-
C879, Revision 3, dated October 9, 2002.
(e) On RB211-535E4-B engines, ultrasonically inspect, and if
required, relubricate using the following Table 5:
Table 5.--RB211-535E4-B
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Initial Repeat
inspection inspection
Engine location within Type action In accordance with within
(CSN) (CSN)
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(1) On-wing................ 17,000. (i) Root Probe, inspect and RB.211-72-C879 Revision 3, 1,200.
3.A.(1).
relubricate, OR............ through 3.A.(7), dated
October 9, 2002..
(ii) Wave Probe............ RB.211-72-C879 Revision 1,000.
3,3.B.(1) through
3.B.(7), dated October 9,
2002..
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[[Page 37738]]
(2) In Shop................ 17,000. Root Probe, inspect and RB.211-72-C879 Revision 1,200.
relubricate.. 3,3.C.(1) through
3.C.(4), dated October 9,
2002..
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Optional Terminating Action
(f) Application of Metco 58 blade root coating using RR SB
RB.211-72-C946, Revision 1, dated August 6, 2002, constitutes
terminating action to the repetitive inspection requirements
specified in paragraphs (b), (c), (d), and (e) of this AD.
Alternative Methods of Compliance
(g) 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 (ECO).
Operators must submit their request through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, ECO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the ECO.
Special Flight Permits
(h) Special flight permits may be issued in accordance with
Sec. Sec. 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 requirements of this AD can be done.
Documents That Have Been Incorporated By Reference
(i) The inspections must be done in accordance with Rolls-Royce
plc mandatory service bulletin RB.211-72-C879, Revision 3, dated
October 9, 2002. 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 plc, PO
Box 31, Derby, England, DE248BJ; telephone: 011-44-1332-242-424;
fax: 011-44-1332-249-936. Copies may be inspected at the FAA, New
England Region, Office of the Regional 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.
Note 4: The subject of this AD is addressed in CAA airworthiness
directive AD 002-01-2000, dated October 9, 2002.
Effective Date
(j) This amendment becomes effective on July 30, 2003.
Issued in Burlington, Massachusetts, on June 13, 2003.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 03-15449 Filed 6-24-03; 8:45 am]
BILLING CODE 4910-13-P