[Federal Register Volume 68, Number 122 (Wednesday, June 25, 2003)]
[Rules and Regulations]
[Pages 37735-37738]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-15449]


-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------


    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
----------------------------------------------------------------------------------------------------------------
                                     Initial                                                           Repeat
                                   inspection                                                        inspection
         Engine location             within            Type action           In accordance with        within
                                      (CSN)                                                             (CSN)
----------------------------------------------------------------------------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------

    (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
----------------------------------------------------------------------------------------------------------------
                                     Initial                                                           Repeat
                                   inspection                                                        inspection
         Engine location             within            Type action           In accordance with        within
                                      (CSN)                                                             (CSN)
----------------------------------------------------------------------------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------

    (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
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                     Initial inspection
         Engine location               within  (CSN)             Type action           In accordance with          Repeat inspection within  (CSN)
--------------------------------------------------------------------------------------------------------------------------------------------------------
(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.
--------------------------------------------------------------------------------------------------------------------------------------------------------


    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
----------------------------------------------------------------------------------------------------------------
                                Initial                                                                Repeat
                              inspection                                                             inspection
      Engine location           within             Type action              In accordance with         within
                                 (CSN)                                                                  (CSN)
----------------------------------------------------------------------------------------------------------------
(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..
----------------------------

[[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..
----------------------------------------------------------------------------------------------------------------

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