
[Federal Register Volume 77, Number 89 (Tuesday, May 8, 2012)]
[Proposed Rules]
[Pages 26998-27001]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-11025]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0428; Directorate Identifier 2011-NM-078-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A330-243, -243F, -342, and -343 airplanes. This proposed 
AD was prompted by reports of cracking of air intake cowls on Rolls-
Royce Trent engines, worn and detached attachment links, and fractured 
thermal anti-ice (TAI) piccolo tubes. This proposed AD would require 
inspecting piccolo tubes, piccolo tube mount links, the aft side of the 
forward bulkhead, and outer boundary angles (OBA) for cracks, 
fractures, and broken links, and corrective actions if necessary. We 
are proposing this AD to prevent degraded structural integrity of the 
engine nose cowl and a broken piccolo tube, which could lead to in-
flight damage of the engine and reduced thermal anti-ice performance.

DATES: We must receive comments on this proposed AD by June 22, 2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For Airbus service information identified in this proposed AD, 
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet 
http://www.airbus.com. For Rolls-Royce service information identified 
in this proposed AD, contact Rolls-Royce Plc, Technical Publications, 
P.O. Box 31, Derby, DE24 8BJ, United Kingdom; telephone 44 (0) 1332 
245882; fax 44 (0) 1332 249936; Internet http://www.Rolls-Royce.com. 
You may review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at the 
FAA, call 425-227-1221.

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 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; fax (425) 227-1149.

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-2012-0428; 
Directorate Identifier 2011-NM-078-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 
Airworthiness Directive 2011-0062, dated April 4, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During shop visit, several primary assembly structures of A330 
aeroplanes Trent 700 [engine] air intake cowl have been found with 
cracks in the forward bulkhead web, web stiffeners and outer 
boundary angles. Several attachment links have been found severely 
worn, and some had become detached. In 2 cases, the Thermal Anti Ice 
(TAI) Piccolo tube was found fractured. Investigations are still 
ongoing to determine the root cause(s).
    If not detected and corrected, a broken Piccolo tube in 
conjunction with forward bulkhead damage could ultimately lead to in 
flight detachment of the outer barrel, which would constitute an 
unsafe condition.
For the reasons described above, this [EASA] AD requires to perform 
inspections of RR [Rolls-Royce] Trent 700 [engine] nose cowls and, 
depending on findings, to do the applicable corrective action(s). 
These inspections include internal inspection of Piccolo tube, 
detailed inspection of Piccolo

[[Page 26999]]

tube mount links, [boroscope] inspection of aft side of forward 
bulkhead and outer boundary angle [for cracks, fractures and broken 
links].

The degraded structural integrity of the engine nose cowl and a broken 
piccolo tube could lead to in-flight damage of the engine and reduced 
thermal anti-ice performance. The corrective action is specified as 
replacing the affected engine air intake cowl with a new or serviceable 
cowl. You may obtain further information by examining the MCAI in the 
AD docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A330-71-3025, 
including Appendices 01 and 02, dated January 10, 2011. Rolls-Royce has 
issued Service Bulletin RB.211-71-AG416, including Appendix 1, dated 
September 3, 2010. The actions described in this service information 
are intended to correct the unsafe condition identified in the MCAI. 
The interval for repetitive inspections of the OBA is between 450 
flight cycles and 5,000 flight cycles depending on crack length; and 
the interval for the repetitive inspections of the forward bulkhead is 
between 400 flight cycles and 5,000 flight cycles depending on crack 
length.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    Figure A-FBBAA--Sheet 03 Flow Chart of Airbus Mandatory Service 
Bulletin A330-71-3025, including Appendix 01, excluding Appendix 02, 
dated January 10, 2011, specifies certain actions based on inspection 
findings of OBA cracking greater than 22 inches or bulkhead cracking 
greater than 13 inches. This proposed AD specifies the actions to be 
done for OBA cracking of 22 inches or greater and bulkhead cracking of 
13 inches or greater.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 14 products of U.S. registry. We also estimate that 
it would take about 10 work-hours per engine to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $11,900 per engine, or $850 per engine.
    In addition, we estimate that any necessary follow-on actions would 
take about 16 work-hours per engine for a cost of $1,360 per engine. We 
have received no definitive data that would enable us to provide 
material cost estimates for the on-condition actions specified in this 
proposed AD. We have no way of determining the number of products that 
may need these actions.

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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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, Incorporation by 
reference, 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:

Airbus: Docket No. FAA-2012-0428; Directorate Identifier 2011-NM-
078-AD.

(a) Comments Due Date

    We must receive comments by June 22, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-243, -243F, -341, -342, and 
-343 airplanes, certificated in any category, all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 71; Engine.

(e) Reason

    This AD was prompted by reports of cracking of air intake cowls 
on Rolls-Royce Trent engines, worn and detached attachment links, 
and fractured thermal anti-ice (TAI) piccolo tubes. We are issuing 
this AD to prevent degraded structural integrity of the engine nose 
cowl and a broken piccolo tube, which could lead to in-flight damage 
of the engine and reduced thermal anti-ice performance.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Piccolo Tube Inspection

    At the applicable time specified in paragraph (g)(1) or (g)(2) 
of this AD, do a boroscope inspection of each air intake cowl 
assembly of each engine to detect cracked or fractured piccolo 
tubes, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A330-71-3025,

[[Page 27000]]

including Appendix 01, excluding Appendix 02, dated January 10, 
2011. If any cracked or fractured piccolo tube is found: Before 
further flight, replace the affected engine air intake cowl with a 
new or serviceable cowl, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-71-3025, 
including Appendix 01, excluding Appendix 02, dated January 10, 
2011.
    (1) For any air intake cowl that has accumulated fewer than 
5,000 flight cycles since its first installation on an airplane as 
of the effective date of this AD: Inspect within 24 months after the 
air intake cowl has accumulated 5,000 total flight cycles.
    (2) For any air intake cowl that has accumulated 5,000 or more 
flight cycles since its first installation on an airplane as of the 
effective date of this AD: Inspect within 24 months after the 
effective date of this AD.

(h) Piccolo Link Inspection

    If the inspection findings of paragraph (g) of this AD indicate 
no cracked or fractured piccolo tube: Before further flight, do a 
boroscope inspection of the piccolo tube links to detect broken 
links, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A330-71-3025, including Appendix 01, 
excluding Appendix 02, dated January 10, 2011. If no broken links 
are found: Before further flight, do the actions required by 
paragraph (i) of this AD.
    (1) If 4 or more broken piccolo tube links are found: Before 
further flight, replace the affected engine air intake cowl with a 
new or serviceable cowl, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-71-3025, 
including Appendix 01, excluding Appendix 02, dated January 10, 
2011.
    (2) If 3 or fewer broken piccolo tube links are found and the 
opposite intake cowl of the same engine has accumulated 5,000 flight 
cycles or less since the cowl was first installed on an airplane: 
Before further flight, do the actions in Figure A-FBBAA-Sheet 03 
Flow Chart of Airbus Mandatory Service Bulletin A330-71-3025, 
including Appendix 01, excluding Appendix 02, dated January 10, 
2011, as required by paragraph (i) of this AD.
    (3) If 3 or fewer broken piccolo tube links are found and the 
opposite intake cowl of the same engine has accumulated more than 
5,000 total flight cycles since the cowl was first installed on an 
airplane: Before further flight, do a boroscope inspection of the 
piccolo tube links of the opposite intake cowl side to detect broken 
links, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A330-71-3025, including Appendix 01, 
excluding Appendix 02, dated January 10, 2011.
    (i) If the inspection findings of the piccolo tube links of the 
opposite intake cowl side indicate no broken piccolo tube links: 
Before further flight, do the actions required by paragraph (i) of 
this AD, ``Repetitive Outer Boundary Angle and Forward Bulkhead 
Inspection.''
    (ii) If the inspection findings of the piccolo tube links of the 
opposite intake cowl side indicate 1 or more broken piccolo tube 
links: Before further flight, do the actions specified in Note 01 of 
Figure A-FBBAA--Sheet 02 Flow Chart of Airbus Mandatory Service 
Bulletin A330-71-3025, including Appendix 01, excluding Appendix 02, 
dated January 10, 2011, at the time specified in Note 01 of Figure 
A-FBBAA--Sheet 02 Flow Chart of Airbus Mandatory Service Bulletin 
A330-71-3025, including Appendix 01, excluding Appendix 02, dated 
January 10, 2011, except for the instructions to ``See Sheet 03''. 
Where Note 01 of Figure A-FBBAA--Sheet 02 Flow Chart of Airbus 
Mandatory Service Bulletin A330-71-3025, including Appendix 01, 
excluding Appendix 02, dated January 10, 2011, specifies to ``See 
Sheet 03'' to do a detailed inspection of the outer boundary angle 
(OBA) and bulkhead as specified in Rolls-Royce Service Bulletin 
RB211-71-AG416, excluding Appendix 1, dated September 3, 2010: This 
AD requires the detailed inspection specified in Figure A-FBBAA--
Sheet 03 Flow Chart of Airbus Mandatory Service Bulletin A330-71-
3025, including Appendix 01, excluding Appendix 02, dated January 
10, 2011, to be done in accordance with paragraph (i) of this AD.

(i) Repetitive Outer Boundary Angle and Forward Bulkhead Inspection

    If the results of the inspection required by paragraph (h) of 
this AD indicate no broken piccolo tube links, or if the 
requirements in paragraph (h)(2) or (h)(3)(ii) of this AD specify to 
do the actions in Figure A-FBBAA--Sheet 03 Flow Chart of Airbus 
Mandatory Service Bulletin A330-71-3025, including Appendix 01, 
excluding Appendix 02, dated January 10, 2011: Before further 
flight, do a boroscope inspection of the OBA and forward bulkhead to 
detect cracks or fractures, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-71-3025, 
including Appendix 01, excluding Appendix 02, dated January 10, 
2011; and the Accomplishment Instructions of Rolls-Royce Service 
Bulletin RB.211-71-AG416, excluding Appendix 1, dated September 3, 
2010.
    (1) If the findings of the inspection are within the allowable 
damage limit, as specified in the Accomplishment Instructions of 
Rolls-Royce Service Bulletin RB.211-71-AG416, excluding Appendix 1, 
dated September 3, 2010: Do the actions in paragraphs (i)(1)(i) and 
(i)(1)(ii) of this AD.
    (i) Repeat the inspection of the OBA and forward bulkhead 
thereafter at the repeat interval specified in Part 3.B. of the 
Accomplishment Instructions of Rolls-Royce Service Bulletin RB.211-
71-AG416, excluding Appendix 1, dated September 3, 2010.
    (ii) Repeat the inspections specified in paragraphs (g) and (h) 
of this AD thereafter at intervals not to exceed 2,500 flight 
cycles.
    (2) If the findings of the inspection are not within the 
allowable damage limit, as specified in the Accomplishment 
Instructions of Rolls-Royce Service Bulletin RB.211-71-AG416, 
excluding Appendix 1, dated September 3, 2010: Do the actions in 
paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
    (i) If any OBA crack is 22 inches or greater, or any forward 
bulkhead crack is 13 inches or greater: Before further flight, 
replace the affected engine air intake cowl with a new or 
serviceable cowl, in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A330-71-3025, including 
Appendix 01, excluding Appendix 2, dated January 10, 2011.
    (ii) If any OBA crack is 15 inches or greater, but less than 22 
inches, or any forward bulkhead crack is 9 inches or greater, but 
less than 13 inches: Within 100 flight cycles, replace the affected 
engine air intake cowl with a new or serviceable cowl, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A330-71-3025, including Appendix 01, excluding Appendix 02, 
dated January 10, 2011.

(j) Repetitive Inspections for Replaced Engine Air Intake Cowl

    If any engine air intake cowl is replaced in accordance with the 
requirements of this AD with a cowl that has less than 5,000 flight 
cycles since the cowl was first installed on an airplane: Repeat the 
inspection required by paragraph (g) of this AD thereafter at the 
compliance time specified in paragraph (g)(1) of this AD.
    (1) If any engine air intake cowl is replaced in accordance with 
the requirements of this AD with a cowl with 5,000 flight cycles or 
more since the cowl was first installed on an airplane: Repeat the 
inspections required by paragraphs (g) and (h) of this AD thereafter 
at intervals not to exceed 2,500 flight cycles.
    (2) If any engine air intake cowl is replaced in accordance with 
the requirements of this AD with a cowl with 5,000 flight cycles or 
more since the cowl was first installed on an airplane: Repeat the 
inspections required by paragraph (i) of this AD thereafter at the 
intervals specified in the Accomplishment Instructions of Rolls-
Royce Service Bulletin RB.211-71-AG416, excluding Appendix 1, dated 
September 3, 2010.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from

[[Page 27001]]

a manufacturer or other source, use these actions if they are FAA-
approved. Corrective actions are considered FAA-approved if they are 
approved by the State of Design Authority (or their delegated 
agent). You are required to assure the product is airworthy before 
it is returned to service.

(l) Related Information

    Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2011-0062, dated April 4, 2011; Airbus Mandatory Service 
Bulletin A330-71-3025, including Appendix 01, excluding Appendix 02, 
dated January 10, 2011; and Rolls-Royce Service Bulletin RB.211-71-
AG416, excluding Appendix 1, dated September 3, 2010; for related 
information.

    Issued in Renton, Washington, on April 29, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2012-11025 Filed 5-7-12; 8:45 am]
BILLING CODE 4910-13-P


