Document ID: FAA-2010-0614-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Rolls-Royce Deutschland Ltd and Co. KG Models BR700-710A1-10, etc. Turbofan Engines
Posted Date: 2010-08-23T04:00Z

[Federal Register: August 23, 2010 (Volume 75, Number 162)]
[Proposed Rules]               
[Page 51693-51696]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23au10-19]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0614; Directorate Identifier 2010-NE-24-AD]
RIN 2120-AA64

 
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG 
Models BR700-710A1-10; BR700-710A2-20; and BR700-710C4-11 Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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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) 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:

    Due to manufacturing problems of BR700-710 HP stage 1 and 2 
turbine discs it was necessary to re-calculate the Declared Safe 
Cyclic Life (DSCL) for all BR700-710 HP turbine discs. The analysis 
concluded that it is required to reduce the approved life limits for 
the HP turbine disc part numbers that are listed in Table 1 and 
Table 2 of this AD (MCAI). Exceeding the revised approved life 
limits could potentially result in non-contained disc failure.

    We are proposing this AD to prevent-failure of the high-pressure 
turbine (HPT) stage 1 and stage 2 discs, uncontained engine failure, 
and damage to the airplane.

DATES: We must receive comments on this proposed AD by October 7, 2010.

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.
    Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, 
Dahlewitz, 15827 Blankenfelde-Mahlow, Germany, telephone: +49 (0) 33-
7086-1883, fax: +49 (0) 33-7086-3276, for the service information 
identified in this proposed AD.

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 (phone (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: Tara Chaidez, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
tara.chaidez@faa.gov; telephone (781) 238-7773; 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

[[Page 51694]]

to an address listed under the ADDRESSES section. Include ``Docket No. 
FAA-2010-0614; Directorate Identifier 2010-NE-24-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 
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).

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, notified us that 
an unsafe condition may exist on Rolls-Royce Deutschland Ltd & Co KG 
Models BR700-710A1-10; BR700-710A2-20; and BR700-710C4-11 turbofan 
engines. The MCAI states:

    Due to manufacturing problems of BR700-710 HP stage 1 and 2 
turbine discs it was necessary to re-calculate the Declared Safe 
Cyclic Life (DSCL) for all BR700-710 HP turbine discs. The analysis 
concluded that it is required to reduce the approved life limits for 
the HP turbine disc part numbers that are listed in Table 1 and 
Table 2 of this AD (MCAI). Exceeding the revised approved life 
limits could potentially result in non-contained disc failure.

    You may obtain further information by examining the MCAI 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 MCAI 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 replacing the HPT stage 1 or HPT stage 2 
discs with serviceable discs at the DSCL as applicable, as listed in 
Table 1 or Table 2 of the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 1,026 BR700-710 engines of U.S. registry. We also 
estimate that no additional labor cost will be incurred to replace the 
discs. The average labor rate is $85 per work-hour. Required parts 
would cost about $6,000 per disc. Based on these figures, we estimate 
the cost of the proposed AD on U.S. operators to be $6,156,000. 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 
airworthiness directive (AD):

Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce 
Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Docket No. FAA-
2010-0614; Directorate Identifier 2010-NE-24-AD.

Comments Due Date

    (a) We must receive comments by October 7, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG 
models BR700-710A1-10, BR700-710A2-20, and BR700-710C4-11 turbofan 
engines with any of the high-pressure turbine (HPT) stage 1 and 
stage 2 discs installed as listed by part number (P/N) in Table 1 
and Table 2 of this AD. These engines are installed on, but not 
limited to, Gulfstream model G-V and GV-SP airplanes, and Bombardier 
model BD-700-1A10 and BD-700-1A11 airplanes.

[[Page 51695]]

    Table 1--Declared Safe Cyclic Life of Affected HPT Stage 1 Discs
------------------------------------------------------------------------
                                                           Declared safe
                                                            cyclic life
      HPT Stage 1 disc p/n             Engine model           (flight
                                                              cycles)
------------------------------------------------------------------------
BRR21215.......................  BR700-710A1-10.........           6,075
BRR21215.......................  BR700-710A2-20.........           5,950
BRR22005.......................  BR700-710A1-10.........           6,200
BRR22005.......................  BR700-710A2-20.........           6,200
BRR22006.......................  BR700-710A1-10.........           6,200
BRR22006.......................  BR700-710A2-20.........           6,200
BRR22007.......................  BR700-710A1-10.........           6,200
BRR22007.......................  BR700-710A2-20.........           6,200
BRR22358.......................  BR700-710A1-10.........           6,200
BRR22358.......................  BR700-710A2-20.........           6,200
BRR23864.......................  BR700-710A1-10.........           6,200
BRR23864.......................  BR700-710A2-20.........           6,200
BRR23884.......................  BR700-710A1-10.........           6,200
BRR23884.......................  BR700-710A2-20.........           6,200
BRR23885.......................  BR700-710A1-10.........           6,200
BRR23885.......................  BR700-710A2-20.........           6,200
BRR23952.......................  BR700-710A1-10.........           6,200
BRR23952.......................  BR700-710A2-20.........           6,200
BRR23952.......................  BR700-710C4-11 (Service           6,200
                                  Bulletin (SB) No. SB-
                                  BR700-72-101466 not
                                  incorporated).
BRR23952.......................  BR700-710C4-11 (SB No.            3,800
                                  SB-BR700-72-101466
                                  incorporated).
BRR23953.......................  BR700-710A1-10.........           6,200
BRR23953.......................  BR700-710A2-20.........           6,200
BRR23953.......................  BR700-710C4-11 (SB No.            6,200
                                  SB-BR700-72-101466 not
                                  incorporated).
BRR23953.......................  BR700-710C4-11 (SB No.            3,800
                                  SB-BR700-72-101466
                                  incorporated).
BRR23954.......................  BR700-710A1-10.........           6,200
BRR23954.......................  BR700-710A2-20.........           6,200
------------------------------------------------------------------------

    Table 2--Declared Safe Cyclic Life of Affected HPT Stage 2 Discs
------------------------------------------------------------------------
                                                           Declared safe
                                                            cyclic life
      HPT Stage 2 disc p/n             Engine model           (flight
                                                              cycles)
------------------------------------------------------------------------
BRR18291.......................  BR700-710A1-10.........           9,300
BRR21214.......................  BR700-710A1-10.........           9,600
BRR21214.......................  BR700-710A2-20.........           9,600
BRR22008.......................  BR700-710A1-10.........          10,500
BRR22008.......................  BR700-710A2-20.........          10,500
BRR22008.......................  BR700-710C4-11 (SB No.           10,500
                                  SB-BR700-72-101466 not
                                  incorporated).
BRR22008.......................  BR700-710C4-11 (SB No.            3,700
                                  SB-BR700-72-101466
                                  incorporated).
BRR22009.......................  BR700-710A1-10.........          10,500
BRR22009.......................  BR700-710A2-20.........          10,500
BRR22009.......................  BR700-710C4-11 (SB No.           10,500
                                  SB-BR700-72-101466 not
                                  incorporated).
BRR22009.......................  BR700-710C4-11 (SB No.            3,700
                                  SB-BR700-72-101466
                                  incorporated).
BRR22010.......................  BR700-710A1-10.........          10,500
BRR22010.......................  BR700-710A2-20.........          10,500
BRR22359.......................  BR700-710A1-10.........          10,500
BRR22359.......................  BR700-710A2-20.........          10,500
------------------------------------------------------------------------

Reason

    (d) 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 states:
    Due to manufacturing problems of BR700-710 HP stage 1 and 2 
turbine discs it was necessary to re-calculate the Declared Safe 
Cyclic Life (DSCL) for all BR700-710 HP turbine discs. The analysis 
concluded that it is required to reduce the approved life limits for 
the HP turbine disc part numbers that are listed in Table 1 and 
Table 2 of this AD (MCAI). Exceeding the revised approved life 
limits could potentially result in non-contained disc failure.
    We are issuing this AD to prevent failure of the HPT stage 1 and 
stage 2 discs, uncontained engine failure, and damage to the 
airplane.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) Within 30 days after the effective date of this AD, or upon 
accumulating the declared safe cyclic life indicated in Table 1 or 
Table 2 of this AD as applicable, whichever occurs later, initially 
replace the HPT stage 1 or HPT stage 2 discs with serviceable discs.
    (2) Thereafter, upon accumulating the declared safe cyclic life 
indicated in Table 1 or Table 2 of this AD, as applicable, 
repetitively replace the HPT stage 1 or HPT stage 2 discs with 
serviceable discs.

FAA AD Differences

    (f) None.

Alternative Methods of Compliance (AMOCs)

    (g) 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.

[[Page 51696]]

Related Information

    (h) Refer to European Aviation Safety Agency AD 2010-0075, dated 
April 20, 2010, and AD 2010-0076, dated April 20, 2010, for related 
information.
    (i) Refer to Rolls-Royce Deutschland Ltd & Co KG SB No. SB-
BR700-72-A900492, dated February 12, 2010, and SB No. SB-BR700-72-
A900497, dated February 12, 2010, for related information. Contact 
Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 
Blankenfelde-Mahlow, Germany, telephone: +49 (0) 33-7086-1883, fax: 
+49 (0) 33-7086-3276, for a copy of this service information.
    (j) Contact Tara Chaidez, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
tara.chaidez@faa.gov; telephone (781) 238-7773; fax (781) 238-7199, 
for more information about this AD.

    Issued in Burlington, Massachusetts, on August 16, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-20757 Filed 8-20-10; 8:45 am]
BILLING CODE 4910-13-P