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[Federal Register: April 2, 2010 (Volume 75, Number 63)]
[Rules and Regulations]               
[Page 16657-16660]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02ap10-7]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1166; Directorate Identifier 2009-NM-107-AD; 
Amendment 39-16255; AD 2010-07-10]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A300 B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) 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:

    One operator reported loss of both pitch trims following 
autopilot disengagement after take off. Subsequent shop findings 
revealed severe damage to the power gears. Mal-phasing between the 
hydraulic motors was suspected to have induced excessive loads into 
the gear train, leading to collapse of one bearing on a shaft of the 
main gear, causing severe tooth damage. The combination of tooth 
damage and gear tilting caused the disconnection of two of the three 
hydraulic motors, resulting in jamming of the THSA [trimmable 
horizontal stabilizer actuator] gearbox and consequent loss of THSA 
control.

[[Page 16658]]

    This condition, if not detected and corrected, could lead to 
further cases of mal-phasing of the hydraulic motors of the THSA, 
causing degradation of the power gears and potentially resulting in 
reduced control of the aeroplane.
* * * * *
We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective May 7, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 7, 2010.

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 December 11, 2009 
(74 FR 65699). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    One operator reported loss of both pitch trims following 
autopilot disengagement after take off. Subsequent shop findings 
revealed severe damage to the power gears. Mal-phasing between the 
hydraulic motors was suspected to have induced excessive loads into 
the gear train, leading to collapse of one bearing on a shaft of the 
main gear, causing severe tooth damage. The combination of tooth 
damage and gear tilting caused the disconnection of two of the three 
hydraulic motors, resulting in jamming of the THSA [trimmable 
horizontal stabilizer actuator] gearbox and consequent loss of THSA 
control.
    This condition, if not detected and corrected, could lead to 
further cases of mal-phasing of the hydraulic motors of the THSA, 
causing degradation of the power gears and potentially resulting in 
reduced control of the aeroplane.
    For the reasons described above, this AD requires repetitive 
checks [on-airplane phasing inspections and magnetic plug 
inspections for metal particles on the drain plug using detailed 
inspection methods] of the THSA and corrective actions [replacement 
of the THSA with a serviceable unit], depending on findings.

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 considered the comment received from the Air Line Pilots 
Association, International (ALPA). ALPA supports the NPRM.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed.

Differences Between This 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 our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Explanation of Change to Costs of Compliance

    Since issuance of the NPRM, we have increased the labor rate used 
in the Costs of Compliance from $80 per work-hour to $85 per work-hour. 
The Costs of Compliance information, below, reflects this increase in 
the specified hourly labor rate.

Costs of Compliance

    We estimate that this AD will affect 12 products of U.S. registry. 
We also estimate that it will take about 5 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD to the U.S. operators to be $5,100, or $425 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 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 the NPRM, 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

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

[[Page 16659]]

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:

2010-07-10 Airbus: Amendment 39-16255. Docket No. FAA-2009-1166; 
Directorate Identifier 2009-NM-107-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 7, 
2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 B2-1C, B2K-3C, B2-203, 
B4-2C, B4-103, and B4-203 airplanes, certificated in any category, 
all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
Controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    One operator reported loss of both pitch trims following 
autopilot disengagement after take off. Subsequent shop findings 
revealed severe damage to the power gears. Mal-phasing between the 
hydraulic motors was suspected to have induced excessive loads into 
the gear train, leading to collapse of one bearing on a shaft of the 
main gear, causing severe tooth damage. The combination of tooth 
damage and gear tilting caused the disconnection of two of the three 
hydraulic motors, resulting in jamming of the THSA [Trimmable 
Horizontal Stabilizer Actuator] gearbox and consequent loss of THSA 
control.
    This condition, if not detected and corrected, could lead to 
further cases of mal-phasing of the hydraulic motors of the THSA, 
causing degradation of the power gears and potentially resulting in 
reduced control of the aeroplane.
    For the reasons described above, this AD requires repetitive 
checks [on-airplane phasing inspections and magnetic plug 
inspections for metal particles on the drain plug using detailed 
inspection methods] of the THSA and corrective actions [replacement 
of the THSA with a serviceable unit], depending on findings.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 4,000 flight hours after the last THSA overhaul or 
within 250 flight hours after the effective date of this AD, 
whichever occurs later: Perform an on-airplane phasing inspection of 
the THSA, and a magnetic plug inspection for metal particles on the 
drain plug of the THSA, using detailed inspection methods, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-27-0201, dated March 9, 2009.
    (i) If the THSA passes the phasing inspection, but the magnetic 
plug inspection reveals metal particles that are equal to or less 
than 1.5 mm (0.059 in.) x 0.5 mm (0.0196 in.), and the depth of the 
particle layer does not exceed 1 mm (0.0393 in.), repeat the 
inspections thereafter at intervals not to exceed 2,500 flight hours 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-27-0201, dated March 9, 2009.
    (ii) If the THSA passes the phasing inspection, but the magnetic 
plug inspection reveals metal particles with dimensions greater than 
1.5 mm (0.059 in.) x 0.5 mm (0.0196 in.), or a layer of particles 
with a depth greater than 1 mm (0.0393 in.) is found, before further 
flight, replace the THSA with a serviceable unit, in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-27-0201, dated March 9, 2009.
    (iii) If the THSA fails the phasing inspection and the magnetic 
plug inspection reveals metal particles that are equal to or less 
than 1.5 mm (0.059 in.) x 0.5 mm (0.0196 in.), and the depth of the 
particle layer does not exceed 1 mm (0.0393 in.), within 500 flight 
hours after the inspection, replace the THSA with a serviceable 
unit, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-27-0201, dated March 9, 2009.
    (iv) If the THSA fails the phasing inspection and the magnetic 
plug inspection reveals metal particles with dimensions greater than 
1.5 mm (0.059 in.) x 0.5 mm (0.0196 in.), or a layer of particles 
with a depth greater than 1 mm (0.0393 in.) is found, before further 
flight, replace the THSA with a serviceable unit, in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-27-0201, dated March 9, 2009.

    Note 1:  For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
a mirror, magnifying lenses, etc., may be necessary. Surface 
cleaning and elaborate procedures may be required.''


    Note 2:  A ``serviceable'' THSA is one that has a correct 
hydraulic motor phasing and no particles or few particles with 
maximum dimensions of 1.5 mm (0.059 in.) x 0.5 mm (0.0196 in.) and a 
layer of particles with a maximum depth of 1 mm (0.0393 in.) found 
on the magnetic plug.

    (2) Within 2,500 flight hours after replacing any THSA, perform 
a phasing inspection of the THSA, and a magnetic plug inspection for 
metal particles on the drain plug of the THSA, as specified in 
paragraph (f)(1) of this AD. Replacing the THSA, as required by 
paragraphs (f)(1)(ii), (f)(1)(iii), and (f)(1)(iv) of this AD, as 
applicable, does not constitute terminating action for the 
repetitive inspections as required by paragraph (f)(1)(i) of this 
AD.
    (3) As of the effective date of this AD, do not install a 
replacement THSA on any airplane, unless it has been inspected in 
accordance with the requirements of paragraphs (f)(1)(i) through 
(f)(1)(iv), as applicable, of this AD.
    (4) Within 3 weeks after removal of a THSA unit from an 
airplane, send it to the THSA manufacturer, Goodrich Actuation 
Systems, Stafford Road Fordhouses, Wolverhampton, West Midlands WV10 
7EH, England.
    (5) Submit a report of the findings (both positive and negative) 
of the inspections required by paragraph (f)(1) of this AD to the 
Manager, Airbus Customer Service Directorate, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex France; telephone +33 5 61 93 33 33; 
telex AIRBU 530526F; fax +33 5 61 93 42 51; at the applicable time 
specified in paragraph (f)(5)(i) or (f)(5)(ii) of this AD. The 
report must include the inspection results (including no findings), 
and replacement or actions to be done.
    (i) For any inspection done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) For any inspection done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

FAA AD Differences

    Note 3:  This AD differs from the MCAI and/or service 
information as follows: No differences.

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, Transport Airplane Directorate, 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: 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. Before 
using any approved AMOC on any airplane to which the AMOC applies, 
notify your principal maintenance inspector (PMI) or principal 
avionics inspector (PAI), as appropriate, or lacking a principal 
inspector, your local Flight Standards 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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

[[Page 16660]]

Related Information

    (h) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2009-0111, dated May 13, 2009; and Airbus Mandatory 
Service Bulletin A300-27-0201, dated March 9, 2009; for related 
information.

Material Incorporated by Reference

    (i) You must use Airbus Mandatory Service Bulletin A300-27-0201, 
including Appendices 1, 2, and 3, dated March 9, 2009, 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 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; e-mail: account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (3) You may review copies of the 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.
    (4) 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 NARA, 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 March 25, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-7371 Filed 4-1-10; 8:45 am]
BILLING CODE 4910-13-P
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