Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Models BR700-710A1-10; BR700-710A2-20; and BR700-710C4-11 Turbofan Engines, 76624-76626 [2010-30832]

Download as PDF 76624 Federal Register / Vol. 75, No. 236 / Thursday, December 9, 2010 / Rules and Regulations Amend: By removing the reference to: And adding in its place: § 1272.3 introductory text .......................................... § 1272.3(b) introductory text ...................................... § 1272.3(b)(2) ............................................................ § 1272.3(b)(3) ............................................................ § 1272.4(a) ................................................................. § 1272.4(a) ................................................................. § 1272.4(b) ................................................................. § 1272.4(b) ................................................................. § 1272.4(c) ................................................................. § 1272.5(a) introductory text ...................................... § 1272.5(a)(4) ............................................................ § 1272.5(a)(5) ............................................................ § 1272.5(b) ................................................................. § 980.4(b) .................................................................. § 950.7 ....................................................................... § 917.4 of this chapter .............................................. § 950.10 ..................................................................... § 980.3 ....................................................................... § 980.5(a)(1) through (4) ........................................... § 950.7(a)(4) .............................................................. § 980.3 ....................................................................... § 980.6 ....................................................................... § 980.3 ....................................................................... § 980.7 ....................................................................... § 980.7 ....................................................................... § 980.6 ....................................................................... § 1272.4(b). § 1266.7. § 917.4 of this title. § 1266.10. § 1272.3. § 1272.5(a)(1) through (4). § 1266.7(a)(4). § 1272.3. § 1272.6. § 1272.3. § 1272.7. § 1272.7. § 1272.6. 17. Amend newly redesignated part 1272 by revising all references to ‘‘Finance Board’’ to read ‘‘FHFA’’. ■ 18. Amend newly redesignated § 1272.1 by adding in correct alphabetical order definitions for ‘‘Bank,’’ ‘‘Bank Act’’ and ‘‘FHFA’’ to read as follows: ■ § 1272.1 Definitions. * * * * * Bank, written in title case, means a Federal Home Loan Bank established under section 12 of the Bank Act, as amended (12 U.S.C. 1432). Bank Act means the Federal Home Loan Bank Act, as amended (12 U.S.C. 1421 through 1449). FHFA means the Federal Housing Finance Agency. * * * * * ■ 19. In newly redesignated § 1272.5, amend paragraphs (a)(5) and (b) by revising the words ‘‘Finance Board’s’’ to read ‘‘FHFA’s’’. Dated: November 30, 2010. Edward J. DeMarco, Acting Director, Federal Housing Finance Agency. [FR Doc. 2010–30519 Filed 12–8–10; 8:45 am] BILLING CODE 8070–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0614; Directorate Identifier 2010–NE–24–AD; Amendment 39– 16538; AD 2010–25–05] erowe on DSK5CLS3C1PROD with RULES RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Models BR700–710A1–10; BR700–710A2–20; and BR700–710C4–11 Turbofan Engines Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Mar<15>2010 14:52 Dec 08, 2010 Jkt 223001 ACTION: Final rule. 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: SUMMARY: 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 noncontained disc failure. We are issuing this AD to preventfailure of the high-pressure turbine (HPT) stage 1 and stage 2 discs, uncontained engine failure, and damage to the airplane. DATES: This AD becomes effective January 13, 2011. 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: Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov; telephone (781) 238–7758; 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 August 23, 2010 (75 FR PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 51693). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that: 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 noncontained disc failure. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance Based on the service information, we estimate that this AD will 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 will cost about $6,000 per disc. Based on these figures, we estimate the cost of the 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, E:\FR\FM\09DER1.SGM 09DER1 Federal Register / Vol. 75, No. 236 / Thursday, December 9, 2010 / Rules and Regulations 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 76625 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. § 39.13 [Amended] 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 (phone (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 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. Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ 2. The FAA amends § 39.13 by adding the following new AD: 2010–25–05 Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Amendment 39– 16538. Docket No. FAA–2010–0614; Directorate Identifier 2010–NE–24–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 13, 2011. Affected ADs (b) None. TABLE 1—DECLARED SAFE CYCLIC LIFE OF AFFECTED HPT STAGE 1 DISCS HPT stage 1 disc P/N erowe on DSK5CLS3C1PROD with RULES BRR21215 BRR21215 BRR22005 BRR22005 BRR22006 BRR22006 BRR22007 BRR22007 BRR22358 BRR22358 BRR23864 BRR23864 BRR23884 BRR23884 BRR23885 BRR23885 BRR23952 BRR23952 BRR23952 ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... BRR23952 BRR23953 BRR23953 BRR23953 BRR23953 BRR23954 BRR23954 ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... VerDate Mar<15>2010 14:52 Dec 08, 2010 Declared safe cyclic life (flight cycles) Engine model Jkt 223001 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710C4–11 porated). BR700–710C4–11 BR700–710A1–10 BR700–710A2–20 BR700–710C4–11 BR700–710C4–11 BR700–710A1–10 BR700–710A2–20 PO 00000 ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... (Service Bulletin (SB) No. SB–BR700–72–101466 not incor- 6,075 5,950 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 (SB No. SB–BR700–72–101466 incorporated) .......................... ..................................................................................................... ..................................................................................................... (SB No. SB–BR700–72–101466 not incorporated) .................... (SB No. SB–BR700–72–101466 incorporated) .......................... ..................................................................................................... ..................................................................................................... 3,800 6,200 6,200 6,200 3,800 6,200 6,200 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\09DER1.SGM 09DER1 76626 Federal Register / Vol. 75, No. 236 / Thursday, December 9, 2010 / Rules and Regulations TABLE 2—DECLARED SAFE CYCLIC LIFE OF AFFECTED HPT STAGE 2 DISCS HPT stage 2 disc P/N BRR18291 BRR21214 BRR21214 BRR22008 BRR22008 BRR22008 BRR22008 BRR22009 BRR22009 BRR22009 BRR22009 BRR22010 BRR22010 BRR22359 BRR22359 ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... ............................................... BR700–710A1–10 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710C4–11 BR700–710C4–11 BR700–710A1–10 BR700–710A2–20 BR700–710C4–11 BR700–710C4–11 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 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 noncontained 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. erowe on DSK5CLS3C1PROD with RULES 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. ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... (SB No. SB–BR700–72–101466 not incorporated) .................... (SB No. SB–BR700–72–101466 incorporated) .......................... ..................................................................................................... ..................................................................................................... (SB No. SB–BR700–72–101466 not incorporated) .................... (SB No. SB–BR700–72–101466 incorporated) .......................... ..................................................................................................... ..................................................................................................... ..................................................................................................... ..................................................................................................... requested using the procedures found in 14 CFR 39.19. 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 BlankenfeldeMahlow, Germany, telephone: +49 (0) 33–7086–1883, fax: +49 (0) 33–7086– 3276, for a copy of this service information. (j) Contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov; telephone (781) 238–7758; fax (781) 238–7199, for more information about this AD. Issued in Burlington, Massachusetts, on November 30, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–30832 Filed 12–8–10; 8:45 am] BILLING CODE 4910–13–P 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 VerDate Mar<15>2010 14:52 Dec 08, 2010 Declared safe cyclic life (flight cycles) Engine model Jkt 223001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 9,300 9,600 9,600 10,500 10,500 10,500 3,700 10,500 10,500 10,500 3,700 10,500 10,500 10,500 10,500 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 30756; Amdt. No. 3402] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. AGENCY: ACTION: Final rule. This establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. SUMMARY: This rule is effective December 9, 2010. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 9, 2010. DATES: E:\FR\FM\09DER1.SGM 09DER1

Agencies

[Federal Register Volume 75, Number 236 (Thursday, December 9, 2010)]
[Rules and Regulations]
[Pages 76624-76626]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-30832]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0614; Directorate Identifier 2010-NE-24-AD; 
Amendment 39-16538; AD 2010-25-05]
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: Final rule.

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

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:

    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 high-pressure 
turbine (HPT) stage 1 and stage 2 discs, uncontained engine failure, 
and damage to the airplane.

DATES: This AD becomes effective January 13, 2011.

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: Mark Riley, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
mark.riley@faa.gov; telephone (781) 238-7758; 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 August 23, 2010 (75 
FR 51693). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
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 will cost 
about $6,000 per disc. Based on these figures, we estimate the cost of 
the 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,

[[Page 76625]]

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 (phone (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:

2010-25-05 Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce 
Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Amendment 39-
16538. Docket No. FAA-2010-0614; Directorate Identifier 2010-NE-24-
AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
13, 2011.

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.

    Table 1--Declared Safe Cyclic Life of Affected HPT Stage 1 Discs
------------------------------------------------------------------------
                                                          Declared safe
     HPT stage 1 disc P/N            Engine model          cyclic life
                                                         (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                     6,200
                                 (Service 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
------------------------------------------------------------------------


[[Page 76626]]


    Table 2--Declared Safe Cyclic Life of Affected HPT Stage 2 Discs
------------------------------------------------------------------------
                                                          Declared safe
     HPT stage 2 disc P/N            Engine model          cyclic life
                                                         (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.

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 Mark Riley, Aerospace Engineer, Engine Certification 
Office, FAA, Engine & Propeller Directorate, 12 New England Executive 
Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov; telephone (781) 
238-7758; fax (781) 238-7199, for more information about this AD.


    Issued in Burlington, Massachusetts, on November 30, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-30832 Filed 12-8-10; 8:45 am]
BILLING CODE 4910-13-P