
[Federal Register: April 3, 2008 (Volume 73, Number 65)]
[Proposed Rules]               
[Page 18220-18222]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03ap08-20]                         

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================



[[Page 18220]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0224; Directorate Identifier 2007-NE-44-AD]
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: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) provided by the aviation 
authority of Germany to identify and correct an unsafe condition on an 
aviation product. The MCAI states the following:

    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 proposing 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: We must receive comments on this proposed AD by May 5, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, 
Room W12-140, 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.

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.

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: 
jason.yang@faa.gov; telephone (781) 238-7747; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0224; 
Directorate Identifier 2007-NE-44-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    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 we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Emergency Airworthiness Directive (EAD) 2007-0152-E, dated June 1, 
2007, to correct an unsafe condition for the specified products. The 
EASA EAD states:

    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.

You may obtain further information by examining the EASA EAD in the AD 
docket.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of 
Germany, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with Germany, they have notified us of the 
unsafe condition described in the EASA EAD and service information 
referenced above. We are proposing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design. This proposed AD would require reducing the published life 
limits of HP Turbine Stage 1 Discs, P/Ns BRH20130 and BRH20131, and HP 
Turbine Stage 2 Discs, P/Ns BRH19423 and BRH19427.

Costs of Compliance

    We estimate that this proposed AD would affect 260 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 1 work-hour per engine to perform the proposed actions and 
that the average labor rate is $80 per work-hour. Based

[[Page 18221]]

on these figures, we estimate the total cost of the proposed 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 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 this proposed 
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 regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

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 FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Rolls-Royce Deutschland Ltd & Co KG: Docket No. FAA-2008-0224; 
Directorate Identifier 2007-NE-44-AD.

Comments Due Date

    (a) We must receive comments by May 5, 2008.

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
----------------------------------------------------------------------------------------------------------------
                                                      Mandatory decreased maximum approved life
                                   -----------------------------------------------------------------------------
                                             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
----------------------------------------------------------------------------------------------------------------
BRH20130..........................        15971        13324        10500        17647         3794         7941
BRH20131..........................        15971        13324        10500        17647         3794         7941
----------------------------------------------------------------------------------------------------------------


                                  High Pressure (HP) Turbine Stage 2 Rotor Disc
----------------------------------------------------------------------------------------------------------------
                                                      Mandatory decreased maximum approved life
                                   -----------------------------------------------------------------------------
                                             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         1165        10893        13461
BRH19427..........................        21165        17800        13372        21165        10893        13461
----------------------------------------------------------------------------------------------------------------



[[Page 18222]]

    Note: Approved lives in the table are in flight cycles

    (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, 
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: jason.yang@faa.gov; 
telephone (781) 238-7747; fax (781) 238-7199, for more information 
about this AD.

    Issued in Burlington, Massachusetts, on March 19, 2008.
Ann C. Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E8-6866 Filed 4-2-08; 8:45 am]

BILLING CODE 4910-13-P
