
[Federal Register: February 19, 2009 (Volume 74, Number 32)]
[Rules and Regulations]               
[Page 7643-7645]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19fe09-2]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0169; Directorate Identifier 2007-NE-45-AD; 
Amendment 39-15819; AD 2009-04-13]
RIN 2120-AA64

 
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG, 
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:

    The application of most recent 3D FEM modeling has resulted in 
the need to reconsider the disc lives as currently shown in the Time 
Limits Manual. The current Post Certification Life Statement for the 
low pressure (LP) compressor (fan) disc assembly revises the 
Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 
flight cycles for both the BR715 LP (fan) disc assembly Part No. (P/
N) BRH10048 and BR715 LP compressor (fan) disc assembly P/N 
BRH19253, when installed in the BR700-715A1-30 engine model and 
operated against the Hawaiian Flight Mission.

We are issuing this AD to prevent uncontained failure of the LP 
compressor (fan) disc assembly and damage to the airplane.

DATES: This AD becomes effective March 26, 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: 
Jason.yang@faa.gov; 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 February 5, 2008 (73 
FR 6638). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    The application of most recent 3D FEM modeling has resulted in 
the need to reconsider the disc lives as currently shown in the Time 
Limits Manual. The current Post Certification Life Statement for the 
low pressure (LP) compressor (fan) disc assembly revises the 
Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 
flight cycles for both the BR715 LP (fan) disc assembly P/N BRH10048 
and BR715 LP compressor (fan) disc assembly P/N BRH19253, when 
installed in the BR700-715A1-30 engine model and operated against 
the Hawaiian Flight Mission.

    This AD requires, within 25 flight cycles after the effective date 
of the AD:
     Amending the Airworthiness Limitations Section (ALS) of 
the Time Limits Manual SUBTASK 05-10-01-860-016, by revising the 
``GIVEN LIFE A1-30 RATING (FLIGHT CYCLES)'' for both the LP compressor 
(fan) disc assembly P/N BRH10048 and LP compressor (fan) disc assembly 
P/N BRH19253 from 33,000 flight cycles to 25,000 flight cycles; and
     Checking the lifing of both the LP compressor (fan) disc 
assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N 
BRH19253 if the relevant compressor (fan) disc assembly is currently 
installed or was previously installed, in the BR700-715A1-30 engine 
model and operated under the Hawaiian Flight Mission; and
     Removing the relevant compressor (fan) disc assembly from 
service before further flight, if the consumed life has exceeded the 
maximum approved life specified in the ALS.

Comments

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

[[Page 7644]]

Request To Change the AD Applicability

    Rolls-Royce Deutschland requests that we change the AD 
applicability from ``This AD applies to Rolls-Royce Deutschland Ltd & 
Co KG (RRD), BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 
turbofan engines, with a low pressure (LP) compressor disc assembly, 
part number (P/N) BRH10048 or P/N BRH19253, when installed in the 
BR700-715A1-30 engine model and operated against the Hawaiian Flight 
Mission'' to ``This AD applies to Rolls-Royce Deutschland Ltd & Co KG 
(RRD), BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan 
engines, with a low pressure (LP) compressor disc assembly, P/N 
BRH10048 or P/N BRH19253''. The commenter states that due to fan module 
mixing between engine models, the AD is applicable to all relevant fan 
assemblies that have, are, could, or will operate against the Hawaiian 
Flight Mission, when installed in the BR710-715A1-30 engine.
    We agree, and changed the AD applicability.

Request To Combine the Compliance Requirements

    Rolls-Royce Deutschland requests that the AD require the operators 
check the lifing of the LP compressor disc assemblies, P/N BRH10048 and 
P/N BRH19253, using the amended Time Limits Manual (TLM), whether 
currently installed or previously installed in the BR700-715A1-30 
engine, and operated under the Hawaiian Flight mission.
    We partially agree. Operators are responsible for following the 
applicable ALS of the TLM to ensure that all critical rotating parts 
are replaced within the life limitations specified in the Manual. 
However, for clarification purposes, we included this action in the AD.

Other AD Changes

    We determined the AD must be complied with, within 25 flight cycles 
after the effective date of the AD, instead of 100 flight cycles after 
the effective date, as proposed, to expeditiously amend the ALS of the 
TLM with life reduction of the relevant fan disk assembly.
    We also require removing fan disk assemblies from service before 
the next flight if their consumed life has exceeded the maximum 
approved life as specified in the ALS of the TLM. All life limited part 
must be removed from service before reaching its declared life in the 
ALS.

Conclusion

    We reviewed the available data, including the comments 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.

Costs of Compliance

    We estimate that this AD will affect about 240 engines installed on 
aircraft of U.S. registry. This LP compressor (fan) disc assembly 
removal does not impose any additional labor costs if performed at the 
time of scheduled engine overhaul. We also estimate that it will take 
about one work-hour per engine to calculate and re-establish the 
achieved cyclic life for an LP compressor (fan) disc assembly, and that 
the average labor rate is $80 per work-hour. We estimate that the 
prorate cost of the life reduction per engine will be $33,000. Total 
cost of this AD is, therefore, $7,939,200.

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 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:

2009-04-13 Rolls-Royce Deutschland Ltd & Co KG (formerly BMW Rolls-
Royce GmbH, and BMW Rolls-Royce Aero Engines): Amendment 39-15819. 
Docket No. FAA-2007-0169; Directorate Identifier 2007-NE-45-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
26, 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, with a low pressure (LP) compressor (fan) disc assembly, 
part number (P/N) BRH10048 or P/N BRH19253. These engines are 
installed on, but not limited to, McDonnell Douglas Corporation 
model 717-200 airplanes.

[[Page 7645]]

Reason

    (d) The mandatory continuous airworthiness information (MCAI) 
states:

    The application of most recent 3D FEM modeling has resulted in 
the need to reconsider the disc lives as currently shown in the Time 
Limits Manual. The current Post Certification Life Statement for the 
low pressure (LP) compressor (fan) disc assembly revises the 
Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 
flight cycles for both the BR715 LP (fan) disc assembly P/N BRH10048 
and BR715 LP compressor (fan) disc assembly P/N BRH19253, when 
installed in the BR700-715A1-30 engine model and operated against 
the Hawaiian Flight Mission.

    This condition, if not corrected, could result in uncontained 
failure of the LP compressor (fan) disc assembly and damage to the 
airplane.

Actions and Compliance

    (e) Within 25 flight cycles after the effective date of this AD, 
do the following actions, unless already done.
    (1) Amend the Airworthiness Limitations Section (ALS) of the 
Time Limits Manual SUBTASK 05-10-01-860-016, by revising the ``GIVEN 
LIFE A1-30 RATING (FLIGHT CYCLES)'' for both the LP compressor (fan) 
disc assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N 
BRH19253 from 33,000 flight cycles to 25,000 flight cycles.
    (2) Check the lifing of both the LP compressor (fan) disc 
assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N 
BRH19253 if the relevant compressor (fan) disc assembly is currently 
installed or was previously installed, in the BR700-715A1-30 engine 
model and operated under the Hawaiian Flight Mission.
    (3) Remove the relevant compressor (fan) disc assembly from 
service before further flight, if the consumed life has exceeded the 
maximum approved life specified in the ALS.

Alternative Methods of Compliance (AMOC)

    (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 MCAI European Aviation Safety Agency AD 2007-0116-
E, dated May 4, 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 February 10, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-3355 Filed 2-18-09; 8:45 am]

BILLING CODE 4910-13-P
