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[Federal Register: February 12, 2010 (Volume 75, Number 29)]
[Rules and Regulations]               
[Page 6849-6851]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12fe10-2]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0613; Directorate Identifier 2009-NM-013-AD; 
Amendment 39-16195; AD 2010-04-02]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A310-221, -222, -322, -
324, and -325 Airplanes, and Model A300 B4-620, B4-622, B4-622R, and 
F4-622R Airplanes, Equipped With Pratt & Whitney PW4000 or JT9D-7R4 
Series Engines

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:

    During the year 2000, life extension exercise programs were 
launched for Airbus A310 and A300-600 aircraft. Certification of 
Extended Service Goal (ESG) is based on analysis, except for fan 
cowl and thrust reverser (T/R) latches, which are always certified 
by tests.
    * * * testing of the T/R door centre latch has shown that this 
does not meet the requirements for ESG.
* * * * *
The unsafe condition is possible failure of the T/R latch and 
detachment of the T/R from the airplane, which could result in 
structural damage and consequent reduced controllability of the 
airplane. We are issuing this AD to require actions to correct the 
unsafe condition on these products.

DATES: This AD becomes effective March 19, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 19, 
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 July 16, 2009 (74 FR 
34516). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    During the year 2000, life extension exercise programs were 
launched for Airbus A310 and A300-600 aircraft. Certification of 
Extended Service Goal (ESG) is based on analysis, except for fan 
cowl and thrust reverser (T/R) latches, which are always certified 
by tests.
    Currently, the Airworthiness Limitation Item (ALI) task 54-50-28 
for engine pylon T/R hinges requires inspection every 1,200 Flight 
Cycles (FC). An analysis performed by Airbus shows that forward and 
aft T/R door latches have been demonstrated successful for ESG, with 
inspection task every 1,200 FC. However, testing of the T/R door 
centre latch has shown that this does not meet the requirements for 
ESG.
    For the reason described above, this EASA AD requires the 
replacement of the T/R centre latches with serialized latches on LH 
[left hand] and RH [right hand] engines and repetitive [detailed] 
inspections [for cracking] of the serialized latches. In addition, 
this AD introduces a life limit of 18,000 FC for the serialized 
centre latches.

The unsafe condition is possible failure of the T/R latch and 
detachment of the T/R from the airplane, which could result in 
structural damage and consequent reduced controllability of the 
airplane. The corrective action includes replacing the T/R latch if any 
surface crack is found during any inspection. 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 comments received.

Support for the NPRM

    FedEx Express has no objections or comments on the content or 
technical details of the NPRM.

Request To Reduce Applicability

    Airbus asks that Model A300 F4-605R airplanes be removed from the 
applicability specified in the NPRM. Airbus states that these airplanes 
are equipped with General Electric CF6-80C2A5 or CF6-80C2A5F engines.
    We agree with Airbus for the reasons provided. The actions required 
by this AD are not applicable to Model A300 F4-605R airplanes and the 
MCAI does not refer to this model; therefore, we have removed that 
model from the applicability of this AD.

Request To Add a Note

    Airbus also recommends that we include a note after paragraph 
(f)(2) of the NPRM that specifies that accomplishing ALI Task 54-50-28, 
which pertains to a detailed inspection of the engine cowl hinge 
fittings LH/RH, can be done when complying with the inspections 
required by paragraph (f)(2) of the AD.
    We agree with the recommendation from Airbus. While not mandatory, 
performing the specified ALI task at the same time as the inspection 
required by paragraph (f)(2) of this AD would be of benefit to 
operators and would help to maintain an acceptable level of safety on 
the airplanes. We have added a new Note 1 to this AD (and renumbered 
subsequent notes) to include this recommendation.

Explanation of Clarification Made to the Service Bulletin References

    In paragraph (f)(2) of the NPRM, we refer to Airbus Mandatory 
Service Bulletins A300-78-6029 and A310-78-2030, both including 
Appendix 1, both dated October 3, 2008, as the appropriate sources of 
service information for doing the inspection. However, the 
Accomplishment Instructions of those service bulletins do not contain 
procedures for doing the inspection, and the Pratt & Whitney service 
bulletins that contain the inspection procedures are referred to only 
in the Reason section of the Airbus service bulletins. Therefore, for 
clarification, we have referenced Pratt & Whitney Service Bulletins 
PW4NAC 78-113 and PW7R4 78-182, both dated August 15, 2005; in 
paragraph (f)(2) of this AD as the appropriate sources of service 
information for doing the inspection.

Explanation of Clarification Made to the NPRM

    We have clarified the inspection requirement contained in the NPRM. 
Whereas the NPRM specifies an ``inspection,'' we have revised this AD 
to

[[Page 6850]]

clarify that our intent is to require a detailed inspection.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

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.

Costs of Compliance

    We estimate that this AD will affect 47 products of U.S. registry. 
We also estimate that it will take about 30 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $80 per work-hour. Required parts will cost about $6,442 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 $415,574, or $8,842 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:

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:

2010-04-02 Airbus: Amendment 39-16195. Docket No. FAA-2009-0613; 
Directorate Identifier 2009-NM-013-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
19, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A310-221, -222, -322, -324, 
and -325 airplanes, and Model A300 B4-620, B4-622, B4-622R, and F4-
622R airplanes, all serial numbers; certificated in any category; 
equipped with Pratt & Whitney PW4000 or JT9D-7R4 series engines.

Subject

    (d) Air Transport Association (ATA) of America Code 78: Engine 
exhaust.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    During the year 2000, life extension exercise programs were 
launched for Airbus A310 and A300-600 aircraft. Certification of 
Extended Service Goal (ESG) is based on analysis, except for fan 
cowl and thrust reverser (T/R) latches, which are always certified 
by tests.
    Currently, the Airworthiness Limitation Item (ALI) task 54-50-28 
for engine pylon T/R hinges requires inspection every 1,200 Flight 
Cycles (FC). An analysis performed by Airbus shows that forward and 
aft T/R door latches have been demonstrated successful for ESG, with 
inspection task every 1,200 FC. However, testing of the T/R door 
centre latch has shown that this does not meet the requirements for 
ESG.
    For the reason described above, this EASA AD requires the 
replacement of the T/R centre latches with serialized latches on LH 
[left hand] and RH [right hand] engines and repetitive [detailed] 
inspections [for cracking] of the serialized latches. In addition, 
this AD introduces a life limit of 18,000 FC for the serialized 
centre latches.

The unsafe condition is possible failure of the T/R latch and 
detachment of the T/R from the airplane, which could result in 
structural damage and consequent reduced controllability of the 
airplane. The corrective action includes replacing the T/R latch if 
any surface crack is found during any inspection.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Before the accumulation of 30,000 total flight cycles since 
first flight of the airplane, or within 1,200 flight cycles after 
the effective date of this AD, whichever occurs later: Replace the 
non-serialized T/R center latch LH (left hand) and RH (right hand) 
sides, having part number (P/N) 221D0029-11 and P/N 221D0029-13, 
with a serialized T/R center latch having P/N 221D0029-15 in

[[Page 6851]]

accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-78-6029 (for Model A300 B4-620, B4-622, B4-
622R, and F4-622R airplanes) or A310-78-2030 (for Model A310-221, -
222, -322, -324, and -325 airplanes), both including Appendix 1, 
both dated October 3, 2008.
    (2) Within 1,200 flight cycles after accomplishing the 
replacement required by paragraph (f)(1) of this AD: Perform a 
detailed inspection for surface cracking of the T/R center 
serialized latches having P/N 221D0029-15, in accordance with the 
Accomplishment Instructions of Pratt &Whitney Service Bulletins 
PW4NAC 78-113 (for airplanes equipped Pratt & Whitney PW4000 series 
engines) and PW7R4 78-182 (for airplanes equipped JT9D-7R4 series 
engines), both dated August 15, 2005; as applicable. If any crack is 
found, before further flight, replace the serialized T/R center 
latch with a new serialized T/R center latch in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-78-6029 or A310-78-2030, both including Appendix 1, both dated 
October 3, 2008; as applicable. Repeat the inspection thereafter at 
intervals not to exceed 1,200 flight cycles.

    Note 1: Concurrent accomplishment of the inspections required by 
paragraph (f)(2) of this AD, with the inspections for engine pylon 
T/R hinges specified by ALI Task 54-50-28, is recommended.

    (3) Before the accumulation of 18,000 total flight cycles since 
accomplishing the most recent replacement required by paragraph 
(f)(1) or (f)(2) of this AD: Replace the serialized T/R center latch 
having P/N 221D0029-15 with a new serialized T/R center latch having 
P/N 221D0029-15 in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A300-78-6029 (for Model A300 
B4-620, B4-622, B4-622R, and F4-622R) or A310-78-2030 (for Model 
A310-221, -222, -322, -324, and -325 airplanes), both including 
Appendix 1, both dated October 3, 2008. Replacement of the center 
latches does not constitute terminating action for the repetitive 
inspections required by paragraph (f)(2) of this AD.

FAA AD Differences

    Note 2: 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.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2008-0226, dated December 19, 2008; and the service 
information contained in Table 1 of this AD; for related 
information.

                  Table 1--Related Service Information
------------------------------------------------------------------------
               Document                               Date
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin      October 3, 2008.
 A300-78-6029, including Appendix 1.
Airbus Mandatory Service Bulletin      October 3, 2008.
 A310-78-2030, including Appendix 1.
Pratt & Whitney Service Bulletin       August 15, 2005.
 PW4NAC 78-113.
Pratt & Whitney Service Bulletin       August 15, 2005.
 PW7R4 78-182.
------------------------------------------------------------------------

Material Incorporated by Reference

    (i) You must use the service information contained in Table 2 of 
this AD to do the actions required by this AD, as applicable, unless 
the AD specifies otherwise.

               Table 2--Material Incorporated by Reference
------------------------------------------------------------------------
               Document                               Date
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin      October 3, 2008.
 A300-78-6029, including Appendix 1.
Airbus Mandatory Service Bulletin      October 3, 2008.
 A310-78-2030, including Appendix 1.
Pratt & Whitney Service Bulletin       August 15, 2005.
 PW4NAC 78-113.
Pratt & Whitney Service Bulletin       August 15, 2005.
 PW7R4 78-182.
------------------------------------------------------------------------

    (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 or 425-227-1152.
    (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 January 28, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-2601 Filed 2-11-10; 8:45 am]
BILLING CODE 4910-13-P
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