[Federal Register Volume 69, Number 119 (Tuesday, June 22, 2004)]
[Rules and Regulations]
[Pages 34563-34565]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-14051]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18024; Directorate Identifier 2003-NE-39-AD; 
Amendment 39-13684; AD 2004-13-03]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce (1971) Limited, Bristol 
Engine Division Model Viper Mk.601-22 Turbojet Engine

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Rolls-Royce (1971) Limited, Bristol Engine Division (RR) Model Viper 
Mk.601-22 turbojet engines. This AD requires reducing the life of 
certain 1st stage turbine rotor blades from 7,000 hours time-in-service 
(TIS) to 4,600 hours TIS, and provides a drawdown schedule for blades 
that have already exceeded the new reduced life limit. This AD results 
from the manufacturer's investigations into failures of 1st stage 
turbine rotor blades. We are issuing this AD to prevent multiple 
failures of 1st stage turbine rotor blades that could result in a dual-
engine shutdown.

DATES: Effective July 7, 2004.
    We must receive any comments on this AD by August 23, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     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, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You can get the service information identified in this AD from 
Rolls-Royce Limited, Bristol Engines Division, Technical Publications 
Department CLS-4, P.O. Box 3, Filton, Bristol, BS34 7QE England; 
telephone 117-979-1234, fax 117-979-7575.
    You may examine the comments on this AD in the AD docket on the 
Internet at http://dms.dot.gov.

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; telephone (781) 238-
7178; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is 
the airworthiness authority for the United Kingdom (UK), recently 
notified the FAA that an unsafe condition may exist on RR model Viper 
Mk.601-22 turbojet engines. The CAA advises that inspections of 1st 
stage turbine rotor blades, part numbers (P/Ns) V926000, V926293, and 
V926319, from engines that were returned from the field have identified 
cracks in the blade airfoil at an increasing rate. Under the current 
requirements to replace the blades at 7,000 hours TIS, the risk of 
dual-engine shutdowns is unacceptable. Reducing the class B life of 
these 1st stage turbine blades, recommended in Chapter 5 of the engine 
manual, from 7,000 hours TIS to a mandatory life limit of 4,600 hours 
TIS reduces the risk of dual-engine shutdowns.

Relevant Service Information

    We have reviewed and approved the technical contents of RR Alert 
Service Bulletin (ASB) 72-A184, dated January 2001, that describes 
procedures for managing engine configurations to reduce the risk of 
dual-engine shutdowns. The CAA classified this service bulletin as 
mandatory and issued AD 004-01-2001 in order to ensure the 
airworthiness of these RR engines in the UK.

Differences Between This AD and the Service Information

    RR ASB 72-A184, dated January 2001, specifies the date of receipt 
of the ASB as the baseline for the compliance time. This AD specifies 
the effective date of this AD as the baseline for the compliance time.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the 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 CAA has kept the FAA 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.

[[Page 34564]]

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other RR Viper Mk.601-22 turbojet engines of the same type 
design. We are issuing this AD to prevent multiple failures of 1st 
stage turbine rotor blades that could result in a dual-engine shutdown. 
This AD:
     Reduces the recommended class B life of certain 1st stage 
turbine blades, P/Ns V926000, V926293 and V926319, from 7,000 hours TIS 
to a mandatory life limit of 4,600 hours TIS, and
     Provides a drawdown schedule for blades that have already 
exceeded the new reduced life limit.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists for making this amendment effective in less than 30 days.

Docket Management System (DMS)

    We have implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, we posted new AD actions on the DMS 
and assigned a DMS docket number. We track each action and assign a 
corresponding Directorate identifier. The DMS docket No. is in the form 
``Docket No. FAA-200X-XXXXX.'' Each DMS docket also lists the 
Directorate identifier (``Old Docket Number'') as a cross-reference for 
searching purposes.

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 submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2004-18024; 
Directorate Identifier 2003-NE-39-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 http://dms.dot.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 DMS Web 
site, anyone can find and read the comments in any of our dockets, 
including 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) or you may visit 
http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You can get more information about plain 
language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the DMS Docket Offices 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Office (telephone (800) 647-5227) is located on 
the plaza level of the Department of Transportation Nassif Building at 
the street address stated in ADDRESSES. Comments will be available in 
the AD docket shortly after the DMS receives them.

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 the regulation:
    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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 adding the following new airworthiness 
directive:

2004-13-03 Rolls-Royce (1971) Limited, Bristol Engine Division: 
Amendment 39-13684. Docket No. FAA-2004-18024; Directorate 
Identifier 2003-NE-39-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 7, 
2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce (1971) Limited, Bristol 
Engine Division (RR) Model Viper Mk.601-22 turbojet engines with 1st 
stage turbine blades, part numbers (P/Ns) V926000, V926293, and 
V926319, installed. These engines are installed on, but not limited 
to, Raytheon HS.125 Series 600 and BH.125 Series 600 airplanes.

Unsafe Condition

    (d) This AD results from the manufacturer's investigations into 
failures of 1st stage turbine rotor blades. We are issuing this AD 
to prevent multiple failures of 1st stage turbine rotor blades that 
could result in a dual-engine shutdown.

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.

New Reduced Life Limit

    (f) Change the RR Time Limits Manual life limit for the 1st 
stage turbine rotor blades, P/Ns V926000, V926293, and V926319, from 
7,000 hours time-in-service (TIS) to 4,600 hours TIS.
    (g) Limit the number of installed engines with 1st stage turbine 
rotor blades that exceed 4,600 hours TIS on the effective date of 
this AD as specified in the following Table 1:

[[Page 34565]]



                       Table 1.--Installed Engines
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   On the effective date of this AD, if                 Then:
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(1) Both engines installed on the airplane  Replace the engine that has
 have 1st stage turbine rotor blades that    the higher blade life
 exceed 5,800 hours TIS.                     within 50 hours TIS or 6
                                             weeks after the effective
                                             date of this AD, whichever
                                             occurs first.
(2) One engine installed on the airplane    Replace the engine that has
 has 1st stage turbine rotor blades that     the higher blade life
 exceed 5,800 hours TIS, and the other       within 100 hours TIS or 4
 engine has 1st stage turbine rotor blades   months after the effective
 that exceed 4,600 hours TIS.                date of this AD, whichever
                                             occurs first.
(3) One engine installed on the airplane    Replace the engine that has
 has 1st stage turbine rotor blades that     the higher blade life
 exceed 5,800 hours TIS, and the other       within 200 hours TIS or 6
 engine has 1st stage turbine rotor blades   months after the effective
 with fewer than 4,600 hours TIS.            date of this AD, whichever
                                             occurs first.
(4) One engine installed on the airplane    Replace the engine that has
 has 1st stage turbine rotor blades that     the higher blade life by
 exceed 4,600 hours TIS, but have fewer      the earliest of:
 than 5,800 hours TIS, and the other        (i) 5,800 hours TIS, or
 engine has 1st stage turbine rotor blades  (ii) Within 200 hours TIS
 with fewer than 4,600 hours TIS.            after the effective date of
                                             this AD, or
                                            (iii) Within 6 months after
                                             the effective date of this
                                             AD.
------------------------------------------------------------------------

    (h) For any engine with 1st stage turbine rotor blades that have 
4,600 hours TIS or fewer on the effective date of this AD, replace 
the blades as specified in (g)(1) through (g)(4) of Table 1 or 
within 3 years after the effective date of this AD, whichever occurs 
earlier.

Installation of Engines After the Effective Date of This AD

    (i) After the effective date of this AD, do not install any 
engine that has 1st stage turbine rotor blades, P/Ns V926000, 
V926293, and V926319, that exceed 4,600 hours TIS, except as allowed 
in Table 1 of this AD.

Alternative Methods of Compliance

    (j) 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

Material Incorporated by Reference

    (k) None.

Related Information

    (l) Civil Aviation Authority airworthiness directive AD 004-01-
2001, dated January 2001, also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on June 16, 2004.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-14051 Filed 6-21-04; 8:45 am]
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