[Federal Register Volume 72, Number 50 (Thursday, March 15, 2007)]
[Rules and Regulations]
[Pages 12077-12080]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-4535]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27360; Directorate Identifier 2007-NM-026-AD; 
Amendment 39-14986; AD 2007-06-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318, A319, A320 and A321 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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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) originated 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:

* * * * *
* * * updates [to the airplane maintenance manual (AMM), engine 
service manual (ESM), and quick engine change kit instruction manual 
(QECKIM)] have inadvertently introduced torque value errors for the 
bolts that attach the forward engine mount to the engine. * * *
* * * * *

[[Page 12078]]

Application of the incorrect torque to the forward engine mount bolts 
during maintenance could result in failure of the forward engine mount 
and possible separation of the engine from the airplane and damage to 
the wing or loss of control of the airplane. This AD requires actions 
that are intended to address the unsafe condition described in the 
MCAI.

DATES: This AD becomes effective March 30, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications, listed in the AD, as of March 30, 
2007.
    We must receive comments on this AD by April 16, 2007.

ADDRESSES: You may send comments by any of the following methods:
     DOT Docket Web Site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Fax: (202) 493-2251.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Federal eRulemaking Portal: http://www.regulations.gov. 
Follow the instructions for submitting comments.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov; or in person at the Docket Management Facility 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 
Office (telephone (800) 647-5227) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. This streamlined process will allow us to adopt 
MCAI safety requirements in a more efficient manner and will reduce 
safety risks to the public. This process continues to follow all FAA AD 
issuance processes to meet legal, economic, Administrative Procedure 
Act, and Federal Register requirements. We also continue to meet our 
technical decision-making responsibilities to identify and correct 
unsafe conditions on U.S.-certificated products.
    This AD references the MCAI and related service information that we 
considered in forming the engineering basis to correct the unsafe 
condition. The AD contains text copied from the MCAI and for this 
reason might not follow our plain language principles.

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 2007-0036R1, dated February 27, 2007 (referred 
to after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    From May 2006, the forward engine mount removal and installation 
procedures (AMM, ESM, QECKIM) have been updated to add removal and 
installation of the support assemblies.
    These updates have inadvertently introduced torque value errors 
for the bolts that attach the forward engine mount to the engine. 
This condition, if not corrected, may have the following 
consequences:

--rupture of bolts and failure of the support assembly due to 
overtorqued bolts;
--reduced safe life of the secondary thrust load path due to low 
torque on monoball housing bolts.

Application of the incorrect torque to the forward engine mount bolts 
during maintenance could result in failure of the forward engine mount 
and possible separation of the engine from the airplane and damage to 
the wing or loss of control of the airplane. The MCAI requires 
inspection, replacement, and re-torque of the affected bolts and 
adjustment of the torque values. You may obtain further information by 
examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued All Operators Telex A320-71A1042, Revision 01, 
dated February 12, 2007. Goodrich has issued All Operators Letter 
CFM56-074, Revision 1, dated February 1, 2007. The actions described in 
this service information are intended to correct the unsafe condition 
identified in the MCAI.

FAA's Determination and Requirements of This 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the AD.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
application of the incorrect torque to the engine mount primary and 
secondary load path bolts during maintenance could result in failure of 
the forward engine mount and possible separation of the engine from the 
airplane and damage to the wing or loss of control of the airplane. 
Therefore, we determined that notice and opportunity for public comment 
before issuing this AD are impracticable and that good cause exists for 
making this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2007-27360; Directorate 
Identifier 2007-NM-026-AD'' at the beginning of your comments.

[[Page 12079]]

We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive about this AD.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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:

2007-06-05 Airbus: Amendment 39-14986. Docket No. FAA-2007-27360; 
Directorate Identifier 2007-NM-026-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
30, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A318-111 and -112; A319-111, 
-112, -113, -114, and -115; A320-111, -211, -212, and -214; and 
A321-111, -112, -211, -212, and -213 airplanes; certificated in any 
category; all serial numbers, which have CFM International CFM56-5A 
or CFM56-5B series engines installed.

Subject

    (d) Powerplant.

Reason

    (e) The mandatory continued airworthiness information (MCAI) 
states:
    From May 2006, the forward engine mount removal and installation 
procedures (airplane maintenance manual (AMM), engine service manual 
(ESM), quick engine change kit instruction manual (QECKIM)) have 
been updated to add removal and installation of the support 
assemblies.
    These updates have inadvertently introduced torque value errors 
for the bolts that attach the forward engine mount to the engine. 
This condition, if not corrected, may have the following 
consequences:

--rupture of bolts and failure of the support assembly due to 
overtorqued bolts;
--reduced safe life of the secondary thrust load path due to low 
torque on monoball housing bolts.

Application of the incorrect torque to the forward engine mount 
bolts during maintenance could result in failure of the forward 
engine mount and possible separation of the engine from the airplane 
and damage to the wing or loss of control of the airplane. The MCAI 
requires inspection, replacement, and re-torque of the affected 
bolts and adjustment of the torque values.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) As of the effective date of this AD:
    (i) Any maintenance on the engine mounts must be performed in 
accordance with correct instructions as identified in the Airbus All 
Operators Telex (AOT) A320-71A1042, Revision 01, dated February 12, 
2007; or Goodrich All Operators Letter (AOL) CFM56-074, Revision 1, 
dated February 1, 2007; and
    (ii) Any forward engine mount support assemblies fitted on an 
engine which is used as replacement must be fitted in accordance 
with correct instructions as identified in Airbus AOT A320-71A1042, 
Revision 01, dated February 12, 2007; or Goodrich AOL CFM56-074, 
Revision 1, dated February 1, 2007.
    (2) For aircraft on which any forward engine mount support 
assembly has been installed or maintained since May 2006 using 
erroneous torque values given in the maintenance data identified in 
paragraph 1. of the Airbus AOT A320-71A1042, Revision 01, dated 
February 12, 2007, or where the use of correct torque values cannot 
be established: Within 20 days after the effective date of this AD, 
accomplish the actions in paragraphs (f)(2)(i), (f)(2)(ii), 
(f)(2)(iii), and (f)(2)(iv) of this AD, as applicable, in accordance 
with the instructions of Airbus AOT A320-71A1042, Revision 01, dated 
February 12, 2007. Aircraft on which no engine removal has been 
performed since aircraft delivery are not affected by this 
paragraph. The alternative procedure given in paragraph 4.2.3 of the 
AOT is acceptable, provided that the nominal torque values specified 
in paragraphs 4.2.1 and 4.2.2 are restored within 120 flight cycles 
after accomplishing paragraph 4.2.3 of the AOT.
    (i) Remove and inspect the following forward engine mount bolts: 
77710-5H6 (AMM item 90) and NAS2815C15H (AMM item 85).
    (ii) If any bolts, 77710-5H6 (AMM item 90), are found broken 
during the above inspection, before further flight, replace the 
affected forward engine mount support assembly (AMM item 75).
    (iii) Replace bolts, 77710-5H6 (AMM item 90) and NAS2815C15H 
(AMM item 85), with new items and torque them to the correct value.
    (iv) Re-torque 77458-7H21 bolts (AMM item 95) and NAS2816C7H 
(AMM item 50) to the correct value.
    (3) Actions done before the effective date of this AD in 
accordance with Airbus AOT A320-71A1042, dated February 5, 2007, are 
acceptable for compliance with the corresponding provisions of 
paragraph (f)(2) of this AD.
    (4) Within 7 days after the inspection, report all findings to 
Airbus Customer Services, Engineering and Technical Support, 
Attention: Mr. J-P Pourtau SEE11; telephone +33 (0) 5 62 11 04 48; 
fax +33 (0) 5 61 93 36 14.

FAA AD Differences

    Note: This AD differs from the MCAI and/ or service information 
as follows: No differences.


[[Page 12080]]



Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. Send information to ATTN: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-2141; fax (425) 227-1149. Before using any AMOC approved 
in accordance with Sec.  39.19 on any airplane to which the AMOC 
applies, notify the appropriate principal inspector in the FAA 
Flight Standards Certificate Holding District Office.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from 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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2007-0036R1, dated February 27, 2007; Airbus 
All Operators Telex A320-71A1042, Revision 01, dated February 12, 
2007; and Goodrich All Operators Letter CFM56-074, Revision 1, dated 
February 1, 2007, for related information.

Material Incorporated by Reference

    (i) You must use Airbus All Operators Telex A320-71A1042, 
Revision 01, dated February 12, 2007; or Goodrich All Operators 
Letter CFM56-074, Revision 1, dated February 1, 2007; as applicable; 
to do the actions required by this AD, unless the AD specifies 
otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    (3) You may review copies at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call (202) 741-6030, 
or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 7, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-4535 Filed 3-14-07; 8:45 am]
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