[Federal Register Volume 74, Number 54 (Monday, March 23, 2009)]
[Rules and Regulations]
[Pages 12086-12087]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-6226]



[[Page 12086]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0224; Directorate Identifier 2007-NE-44-AD; 
Amendment 39-15860; AD 2009-07-01]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG 
(RRD) BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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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:

    It is necessary to change the limits of the High Pressure (HP) 
Turbine Stage 1 and Stage 2 Rotor Discs. The maximum approved life 
of these discs is decreased for all flight missions.
    This Emergency Airworthiness Directive (EAD) has been raised to 
instruct mandatory decreased maximum approved lives in the BR715 
Time Limits Manual (TLM) T-715-3BR for the HP Turbine Stage 1 Rotor 
Disc for both Part No. BRH20130 and Part No. BRH20131 and of the 
High Pressure (HP) Turbine Stage 2 Rotor Disc for both Part No. 
BRH19423 and Part No. BRH19427 for all flight missions. The life 
limits are decreased by the same proportion for all flight missions, 
thus back to birth pro-rata calculations due to the life limit 
changes are not necessary.

We are issuing this AD to prevent rotating parts that may have exceeded 
their low-cycle fatigue life limits from failing, which could result in 
uncontained engine failure and subsequent damage to the airplane.

DATES: This AD becomes effective April 27, 2009.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; telephone (781) 238-7747; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

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 April 3, 2008 (73 FR 
18220). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    It is necessary to change the limits of the High Pressure (HP) 
Turbine Stage 1 and Stage 2 Rotor Discs. The maximum approved life 
of these discs is decreased for all flight missions.
    This Emergency Airworthiness Directive (EAD) has been raised to 
instruct mandatory decreased maximum approved lives in the BR715 
Time Limits Manual (TLM) T-715-3BR for the HP Turbine Stage 1 Rotor 
Disc for both Part No. BRH20130 and Part No. BRH20131 and of the 
High Pressure (HP) Turbine Stage 2 Rotor Disc for both Part No. 
BRH19423 and Part No. BRH19427 for all flight missions. The life 
limits are decreased by the same proportion for all flight missions, 
thus back to birth pro-rata calculations due to the life limit 
changes are not necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Correction to Table

    One commenter, Rolls-Royce Deutschland Ltd & Co KG, states that in 
the 2nd table following paragraph (e)(1), in the lower half, fifth 
column, ``1165'' should be corrected to read ``21165''.
    We agree and made the correction in the AD.

Change to Table Headings

    Since we issued the proposed AD, we determined that the headings in 
the tables following paragraph (e)(1), of ``Mandatory Decreased Maximum 
Approved Life'' are not sufficiently clear. We changed those headings 
to ``Declared Safe Cyclic Life, in Flight Cycles'', in the AD.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Cost of Compliance

    We estimate that this AD will affect 260 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 
one work-hour per engine to perform the actions and that the average 
labor rate is $80 per work-hour. Based on these figures, we estimate 
the total cost of the AD to U.S. operators to be $20,800. Our cost 
estimate is exclusive of possible warranty coverage.

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 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 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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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 AD, the regulatory evaluation, 
any comments received, and

[[Page 12087]]

other information. The street address for the Docket Operations office 
(telephone (800) 647-5527) is provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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 AD:

2009-07-01 Rolls-Royce Deutschland Ltd & Co KG (formerly BMW Rolls-
Royce GmbH, formerly BMW Rolls-Royce Aero Engines): Amendment 39-
15860. Docket No. FAA-2008-0224; Directorate Identifier 2007-NE-44-
AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective April 
27, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) 
BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. 
These engines are installed on, but not limited to, McDonnell 
Douglas Model 717-200 airplanes.

Reason

    (d) It is necessary to change the limits of the High Pressure 
(HP) Turbine Stage 1 and Stage 2 Rotor Discs. The maximum approved 
life of these discs is decreased for all flight missions.
    This Emergency Airworthiness Directive (EAD) has been raised to 
instruct mandatory decreased maximum approved lives in the BR715 
Time Limits Manual (TLM) T-715-3BR for the HP Turbine Stage 1 Rotor 
Disc for both Part No. BRH20130 and Part No. BRH20131 and of the 
High Pressure (HP) Turbine Stage 2 Rotor Disc for both Part No. 
BRH19423 and Part No. BRH19427 for all flight missions. The life 
limits are decreased by the same proportion for all flight missions, 
thus back to birth pro-rata calculations due to the life limit 
changes are not necessary.
    We are issuing this AD to prevent rotating parts that may have 
exceeded their low-cycle fatigue life limits from failing, which 
could result in uncontained engine failure and subsequent damage to 
the airplane.

Actions and Compliance

    (e) No later than 30 days after the effective date of this AD 
the following mandatory actions need to be completed for each 
individual BR700-715 HP Turbine Stage 1 Rotor Disc for both Part No. 
BRH20130 and Part No. BRH20131 and High Pressure (HP) Turbine Stage 
2 Rotor Disc for both Part No. BRH19423 and Part No. BRH19427 
installed in a BR700-715A1-30, B1-30 or C1-30 engine:
    (1) Identify the mandatory decreased maximum approved life for 
the HP Turbine Stage 1 and Stage 2 Rotor Discs listed in the tables 
below:

----------------------------------------------------------------------------------------------------------------
 High Pressure (HP) Turbine Stage 1 Rotor Disc             Declared Safe Cyclic Life, in Flight Cycles
----------------------------------------------------------------------------------------------------------------
                                                      Engine Thrust Rating            Engine Flight Mission
                                               -----------------------------------------------------------------
                   Part No.                                                                              C1-30
                                                  A1-30      B1-30      C1-30      A1-30      C1-30     derated
                                                  Design     Design     Design    Hawaiian   Tropical   Tropical
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BRH20130......................................      15971      13324      10500      17647       3794       7941
BRH20131......................................      15971      13324      10500      17647       3794       7941
----------------------------------------------------------------------------------------------------------------


----------------------------------------------------------------------------------------------------------------
 High Pressure (HP) Turbine Stage 2 Rotor Disc             Declared Safe Cyclic Life, in Flight Cycles
----------------------------------------------------------------------------------------------------------------
                                                      Engine Thrust Rating            Engine Flight Mission
                                               -----------------------------------------------------------------
                   Part No.                                                                              C1-30
                                                  A1-30      B1-30      C1-30      A1-30      C1-30     derated
                                                  Design     Design     Design    Hawaiian   Tropical   Tropical
----------------------------------------------------------------------------------------------------------------
BRH19423......................................      21165      17800      13372      21165      10893      13461
BRH19427......................................      21165      17800      13372      21165      10893      13461
----------------------------------------------------------------------------------------------------------------

    (2) Record the mandatory maximum approved life in the applicable 
lifing documentation. It is mandatory to use the values given in the 
two tables in step (e)(1) of this AD.

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Engine Certification Office, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.

Related Information

    (g) Refer to EASA Emergency Airworthiness Directive 2007-0152-E 
(corrected), dated June 1, 2007, for related information.
    (h) Contact Jason Yang, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: [email protected]; 
telephone (781) 238-7747; fax (781) 238-7199, for more information 
about this AD.

Material Incorporated by Reference

    (i) None.

    Issued in Burlington, Massachusetts, on March 17, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
 [FR Doc. E9-6226 Filed 3-20-09; 8:45 am]
BILLING CODE 4910-13-P