[Federal Register Volume 77, Number 152 (Tuesday, August 7, 2012)]
[Rules and Regulations]
[Pages 46935-46937]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-18579]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0414; Directorate Identifier 2011-NM-210-AD; 
Amendment 39-17138; AD 2012-15-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) certain 
Airbus Model A310-203, -221, and -222 airplanes. This AD was prompted 
by the manufacturer re-classifying slat extension eccentric bolts as 
principal structural elements with replacement due at or before their 
calculated fatigue lives. This AD replaces certain slat extension 
eccentric bolts with new bolts. We are issuing this AD to prevent 
fatigue cracking, which could result in the loss of structural 
integrity of the airplane.

DATES: This AD becomes effective September 11, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 11, 
2012.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

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 May 2, 2012 (77 FR 
25930). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Slat extension eccentric bolts have been re-classified as 
Principal Structural Elements (PSE). As a result, associated fatigue 
lives will be published in the Airbus A310 Airworthiness Limitations 
Section (ALS) Part 1 and bolts must be replaced at or before their 
calculated fatigue lives.
    The slat extension eccentric bolt Part Number (P/N) 
A5786451220800 installed at slat 2, track 6 of the left hand (LH) 
and right hand (RH) wings is manufactured by SONACA, but some bolts 
with the same P/N, manufactured by FOKKER, may have been installed 
on A310-200 series aeroplanes and are identical in appearance. The 
calculated fatigue life of the FOKKER bolt is lower than that of the 
SONACA equivalent bolt.
    The difference between the FOKKER and SONACA bolt cannot be 
distinguished by a visual inspection. To remedy this, the SONACA 
bolt part number was changed from P/N A5786451220800 to P/N 
A5784307920000.
    Failure to replace the bolts within the new fatigue life limits 
constitutes an unsafe condition.
    For the reasons described above, this [EASA] AD requires the 
replacement of all slat extension eccentric bolts, P/N 
A5786451220800, with slat extension eccentric bolts P/N 
A5784307920000 at the slat 2 tracks 4, 6 and 7 positions, as well as 
at the slat 3 track 8 position, on both LH and RH wings.
    In addition, it is required to replace the slat extension 
eccentric bolt P/N A57843624200 at slat 2 track 5 with a bolt P/N 
A57843624202.

Required actions also include a concurrent inspection of the removed 
bolts for cracking. If cracking is found, certain bolts at slat 2 track 
5 are replaced with new bolts before further flight. If cracking is not 
found, certain bolts at slat 2 track 5 are replaced with new bolts at 
35,900 total flight cycles or 71,800 total flight hours, whichever 
occurs first. The unsafe condition is fatigue cracking, which could 
result in the loss of structural integrity of the airplane. You may 
obtain further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (77

[[Page 46936]]

FR 25930, May 2, 2012) 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

    We estimate that this AD will affect 48 products of U.S. registry. 
We also estimate that it will take about 12 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $35,365 per 
product. Where the service information lists required parts costs that 
are covered under warranty, we have assumed that there will be no 
charge for these parts. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, we estimate the cost of this AD to the 
U.S. operators to be $1,746,480, or $36,385 per product.

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 that 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);
    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 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 the NPRM (77 FR 25930, May 2, 2012), 
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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    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:

2012-15-09 Airbus: Amendment 39-17138. Docket No. FAA-2012-0414; 
Directorate Identifier 2011-NM-210-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective September 
11, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A310-203, -221, and -222 
airplanes; certificated in any category; all manufacturer serial 
numbers (MSN), except airplanes having MSN 0415, 0419, 0424, 0427, 
0430, 0454, 0468, 0486, and 0487.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by the manufacturer re-classifying slat 
extension eccentric bolts as principal structural elements (PSEs) 
with replacement due at or before their calculated fatigue lives. We 
are issuing this AD to prevent fatigue cracking, which could result 
in the loss of structural integrity of the airplane.

(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) Bolt Replacement at Slat 2 Track 6 and Visual Inspection

    (1) At the later of the times specified in paragraphs (g)(1)(i) 
and (g)(1)(ii) of this AD: Replace the slat extension eccentric 
bolts having part number (P/N) A5786451220800 at slat 2 track 6 on 
both wings with bolts having P/N A5784307920000, in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-57-2043, Revision 05, dated September 29, 2010.
    (i) Before the accumulation of 14,000 total flight cycles or 
19,000 total flight hours, whichever occurs first.
    (ii) Within 6 months after the effective date of this AD.
    (2) Concurrently with the actions specified in paragraph (g)(1) 
of this AD: Do a general visual inspection of the removed slat 
extension eccentric bolts having P/N A5786451220800 to detect 
cracking, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A310-57-2043, Revision 05, dated 
September 29, 2010.
    (i) If any cracking is found during the inspection required by 
paragraph (g)(2) of this AD: Before further flight, replace the slat 
extension eccentric bolt having P/N A57843624200 at slat 2 track 5, 
on the right or left wing as applicable, with a bolt having P/N 
A57843624202, in accordance with Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A310-57-2099, dated July 22, 2011.
    (ii) If no cracking is found during the inspection required by 
paragraph (g)(2) of this AD: Before the accumulation of 35,900 total 
flight cycles or 71,800 total flight hours, whichever occurs first, 
replace the slat extension eccentric bolt having P/N A57843624200 at 
slat 2 track 5, on the right or left wing as applicable, with a bolt 
having P/N A57843624202, in accordance with Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-57-2099, 
dated July 22, 2011.

(h) Bolt Replacement at Slat 2 Track 4 and Track 7, and Slat 3 Track 8

    Within 30 months after the effective date of this AD: Replace 
the slat extension eccentric bolts having P/N A5786451220800 at slat 
2 track 4 and track 7, and slat 3 track 8, on both wings, with bolts 
having P/N A5784307920000, in accordance with the

[[Page 46937]]

Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-57-2098, dated July 22, 2011.

(i) Parts Installation Prohibition

    After modification of an airplane as required by this AD, do not 
install any slat extension eccentric bolt having P/N A5786451220800 
on any airplane.

(j) 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: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. 
Information may be emailed to: [email protected]. 
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 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.

(k) Related Information

    Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2011-0187, dated September 27, 2011, and the following 
service information, for related information.
    (1) Airbus Mandatory Service Bulletin A310-57-2043, Revision 05, 
dated September 29, 2010.
    (2) Airbus Mandatory Service Bulletin A310-57-2098, dated July 
22, 2011.
    (3) Airbus Mandatory Service Bulletin A310-57-2099, dated July 
22, 2011.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Mandatory Service Bulletin A310-57-2043, Revision 05, 
dated September 29, 2010.
    (ii) Airbus Mandatory Service Bulletin A310-57-2098, dated July 
22, 2011.
    (iii) Airbus Mandatory Service Bulletin A310-57-2099, dated July 
22, 2011.
    (3) For Airbus service information identified in this AD, Airbus 
SAS-EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 
44 51; email [email protected]; Internet http://www.airbus.com.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on July 20, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-18579 Filed 8-6-12; 8:45 am]
BILLING CODE 4910-13-P