Airworthiness directives: Rolls-Royce plc,
[Federal Register: October 25, 2007 (Volume 72, Number 206)]
[Proposed Rules]
[Page 60606-60609]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25oc07-28]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA-2007-29343; Directorate Identifier 2000-NE-13-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B- 37, and RB211-535E4-B-75 series turbofan engines. That AD requires initial and repetitive ultrasonic inspections of installed low pressure compressor (LPC) fan blade roots on-wing and during overhaul, and relubrication according to accumulated life cycles. That AD also introduces an alternative technique to ultrasonically inspect installed fan blades on-wing using a surface wave ultrasonic probe. Also, that AD introduces application of Metco 58 blade root coating as an optional terminating action. This proposed AD would require the same actions but would add compliance paragraphs to relax the compliance schedule for repetitive inspections for RB211-535E4 engines operating in flight profiles A and B, if certain requirements are met. This proposed AD results from RR issuing Mandatory Service Bulletin (MSB) No. RB.211-72- C879, Revision 5. That MSB introduces a relaxed repetitive compliance schedule for RB211-535E4 engines operating in flight profiles A and B, if certain requirements are met. We are proposing this AD 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: We must receive any comments on this proposed AD by December 24, 2007.
ADDRESSES: Use one of the following addresses to comment on this proposed AD.
Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of Transportation, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 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: 011-44-1332-242-424; fax: 011-44-1332-249-936 for the service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; e-mail: ian.dargin@faa.gov; telephone: (781) 238-7178; fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ``Docket No. FAA-2007-29343; Directorate Identifier 2000-NE-13-AD'' in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments.
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We will post all comments we receive, without change, to http://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 proposed 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 http://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 proposed 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.
Discussion
On January 18, 2005, we issued AD 2005-02-05, Amendment 39-13950 (70 FR 3863, January 27, 2005). That AD requires initial and repetitive ultrasonic inspections of installed LPC fan blade roots on-wing and during overhaul using a surface wave ultrasonic probe, and relubrication according to accumulated life cycles. That AD also adds the application of Metco 58 blade root coating as an optional terminating action. That AD results from RR issuing MSB No. RB.211-72- C879, Revision 4, which contains revised Accomplishment Instructions and consumable materials list.
Actions Since We Issued AD 2005-02-05
Since we issued AD 2005-02-05, Rolls-Royce plc updated MSB No. RB.211-72-C879, Revision 4, dated April 2, 2004, to Revision 5, dated March 8, 2007, for RR RB211 series turbofan engines. Revision 5 relaxes the compliance for repetitive inspections for RB211-535E4 engines operating in flight profiles A and B, if certain requirements are met.
Clarification Changes
Also, as clarification, we changed the Table 4 initial compliance from ``65% hard life'' to ``within 350 cycles after achieving 65% hard life''. These changes better reflect the proposed AD wording, with the latest MSB.
Relevant Service Information
We have reviewed and approved the technical contents of Rolls-Royce plc MSB No. RB.211-72-C879, Revision 5, dated March 8, 2007. That MSB describes procedures for ultrasonic inspection of high cyclic life blades on-wing with either the LPC fan blades in place or removed from the LPC. The Civil Aviation Authority (CAA), which is the airworthiness authority for the United Kingdom (UK), classified the original issue of the service bulletin as mandatory and issued AD 002-01-2000 to ensure the airworthiness of these RR engines in the UK.
Bilateral Agreement Information
This engine model is manufactured in UK 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 UK kept us informed of the situation described above. We have examined the findings of the CAA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. We are proposing this AD, which would require initial and repetitive ultrasonic inspection of installed LPC fan blade roots on-wing and during overhaul using a surface wave ultrasonic probe, and relubrication according to accumulated life cycles. This proposed AD would also maintain the application of Metco 58 blade root coating as an optional terminating action. The proposed AD would require that you do these actions using the service information described previously.
Costs of Compliance
We estimate that this proposed AD would affect 788 engines installed on airplanes of U.S. registry. We also estimate that it would take about 7 work-hours per engine to perform the proposed actions, and that the average labor rate is $80 per work-hour. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $358,540.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed AD:
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Is not a ``significant regulatory action'' under Executive Order 12866;
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Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and
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Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration
[[Page 60608]]
proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
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The FAA amends Sec. 39.13 by removing Amendment 39-13950 (70 FR 3863, January 27, 2005) and by adding a new airworthiness directive, to read as follows:
Rolls-Royce plc: Docket No. FAA-2007-29343; Directorate Identifier 2000-NE-13-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by December 24, 2007.
Affected ADs
(b) This AD revises AD 2005-02-05, Amendment 39-13950.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) 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
Unsafe Condition
(d) This AD results from RR issuing Mandatory Service Bulletin (MSB) No. RB.211-72-C879, Revision 5, that introduces a relaxed repetitive compliance schedule for RB211-535E4 engines operating in flight profiles A and B, if certain requirements are met. We are issuing this AD to detect cracks in low pressure compressor (LPC) fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
(f) If you have a full set of fan blades, modified using RR Service Bulletin No. RB.211-72-C946, Revision 2, dated September 26, 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.
(g) On RB211-535E4 engines, operated to Flight Profile A, ultrasonically inspect, and if required, relubricate using the following Table 2:
Table 2.--RB211-535E4 Flight Profile A
Initial inspection
In accordance with
Engine location within cycles-
Type action
mandatory service Repeat inspection since-new (CSN)
bulletin (MSB)
within (CSN)
(1) On-wing...........
17,350 (i) Root Probe,
RB.211-72-C879
1,400 inspect and
Revision 5, 3.A.(1) relubricate, OR
through 3.A.(7), dated March 8, 2007. .................. (ii) Wave Probe....... RB.211-72-C879
1,150 Revision 5, 3.B.(1) through 3.B.(7), dated March 8, 2007. (2) In Shop...........
17,350 Root Probe, inspect RB.211-72-C879
1,400 and relubricate.
Revision 5, 3.C.(1) through 3.C.(4), dated March 8, 2007.
(h) 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 inspection
Repeat inspection
Engine location
within (CSN)
Type action
In accordance with MSB within (CSN)
(1) On-wing............
12,350 (i) Root Probe, inspect RB.211-72-C879
850 and relubricate, OR Revision 5, 3.A.(1) through 3.A.(7), dated March 8, 2007. .................. (ii) Wave Probe........ RB.211-72-C879
700 Revision 5, 3.B.(1) through 3.B.(7), dated March 8, 2007. (2) In Shop............
12,350 Root Probe, inspect and RB.211-72-C879
850 relubricate.
Revision 5, 3.C.(1) through 3.C.(4), dated March 8, 2007.
[[Page 60609]]
(i) 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
In accordance with Repeat inspection Engine location
within (CSN)
Type action
MSB
within (CSN)
(1) On-wing.............. 350 cycles after (i) Root Probe, RB.211-72-C879
As current flight achieving 65% hard inspect and
Revision 5, 3.A.(1) profile. See life (To calculate, relubricate, OR through 3.A.(7), paragraphs (j) and see MSB Compliance
dated March 8, 2007. (k) of this AD. Section 1.C.(4)). (ii) Wave Probe..... RB.211-72-C879
As current flight Revision 5, 3.B.(1) profile. See through 3.B.(7), paragraphs (j) and dated March 8, 2007. (k) of this AD. (2) In Shop.............. 350 cycles after Root Probe, inspect RB.211-72-C879
As current flight achieving 65% hard and relubricate. Revision 5, 3.C.(1) profile. See life (To calculate,
through 3.C.(4), paragraphs (j) and see MSB Compliance
dated March 8, 2007. (k) of this AD. Section 1.C.(4)).
(j) For RB.211-535E4 engines that are currently flying in Profile A, if the initial inspection is completed before X minus 1,400 cycles then the next inspection may be delayed to X, where X is 65% of the revised life limit.
(k) For RB.211-535E4 engines that are currently flying in Profile B, if the initial inspection is completed before X minus 850 cycles then the next inspection may be delayed to X, where X is 65% of the revised life limit.
(l) Fan blades that have been operated within RB.211-535E4 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 5, dated March 8, 2007.
(m) On RB.211-535E4-B engines, ultrasonically inspect, and if required, relubricate using the following Table 5:
Table 5.--RB211-535E4-B
Initial inspection
Repeat inspection
Engine location
within (CSN)
Type action
In accordance with MSB within (CSN)
(1) On-wing............
17,000 (i) Root Probe, inspect RB.211-72-C879
1,200 and relubricate, OR Revision 5, 3.A.(1) through 3.A.(7), dated March 8, 2007. (ii) Wave Probe........ RB.211-72-C879
1,000 Revision 5, 3.B.(1) through 3.B.(7), dated March 8, 2007. (2) In Shop............
17,000 Root Probe, inspect and RB.211-72-C879
1,200 relubricate.
Revision 5, 3.C.(1) through 3.C.(4), dated March 8, 2007.
Optional Terminating Action
(n) Application of Metco 58 blade root coating using RR SB No. RB.211-72-C946, Revision 2, dated September 26, 2002, constitutes terminating action to the repetitive inspection requirements specified in paragraphs (g), (h), (i), and (k) of this AD.
Alternative Methods of Compliance
(o) 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.
Previous Credit
(p) Previous credit is allowed for initial and repetitive inspections performed using AD 2003-12-15 (Amendment 39-13200, 68 FR 37735, June 25, 2003), RR MSB No. RB.211-72-C879, Revision 3, dated October 9, 2002, and RR MSB No. RB.211-72-C879, Revision 4, dated April 2, 2004.
Related Information
(q) CAA airworthiness directive AD 002-01-2000, dated October 9, 2002, also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on October 18, 2007. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7-20999 Filed 10-24-07; 8:45 am]
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