[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)]
[Proposed Rules]
[Pages 3346-3348]
[FR Doc No: 2016-00944]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0459; Directorate Identifier 2015-NM-081-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-10-
03, for certain Airbus Model A330-200 and -300 series airplanes, and
Model A340-200 and -300 series airplanes. AD 2015-10-03 currently
requires a detailed inspection for visible chrome of each affected main
landing gear (MLG) sidestay upper cardan pin, associated nuts, and
retainer assembly; pin replacement if needed; measurement of cardan pin
clearance dimensions (gap check); corrective actions if necessary; and
a report of all findings. Since we issued AD 2015-10-03, further
investigation concluded that the reported MLG sidestay upper cardan pin
migration event had been caused by corrosion due to lack of jointing
compound and inadequate sealant application during the MLG
installation. This proposed AD would require a detailed inspection of
the upper cardan pin and nut threads for any corrosion, pitting, or
thread damage, and if necessary, replacement of the cardan pin and nut
threads. This proposed AD would also revise the applicability to
include additional airplane models. We are proposing this AD to detect
and correct migration of the sidestay upper cardan pin, which could
result in disconnection of the sidestay upper arm from the airplane
structure, and could result in a landing gear collapse and consequent
damage to the airplane and injury to occupants.

DATES: We must receive comments on this proposed AD by March 7, 2016.

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:<PHONE_NUMBER>.
     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 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<EMAIL_ADDRESS>Internet http://www.airbus.com. You may view this referenced 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0459; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone<PHONE_NUMBER>) 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, WA 98057-3356; telephone<PHONE_NUMBER>;
fax<PHONE_NUMBER>.

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-2016-0459;
Directorate Identifier 2015-NM-081-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

    On April 30, 2015, we issued AD 2015-10-03, Amendment 39-18158 (80
FR 30608, May 29, 2015). AD 2015-10-03 requires actions intended to
address an unsafe condition on certain Airbus Model A330-200 and -300
series airplanes, and Model A340-200 and -300 series airplanes.
    Since we issued AD 2015-10-03, Amendment 39-18158 (80 FR 30608, May
29, 2015), further investigation concluded that the reported MLG
sidestay upper cardan pin migration event had been caused by corrosion
due to lack of jointing compound and inadequate sealant application
during the MLG installation. Therefore, this issue affects any MLG that
had an upper cardan pin replacement or reinstallation, regardless of
MLG overhaul. Any corrosion on the upper cardan pin and nut threads
would not have been detected during the currently required detailed
inspection.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent

for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0079, dated May 7, 2015 (referred to after
this as the Mandatory Continuing Airworthiness Information, or ``the
MCAI''), to correct an unsafe condition for certain Airbus Model A330-
200 and -300 series airplanes, Model A340-200 and -300 series
airplanes, and Model A340-541 and -642 airplanes. The MCAI states:

    An A330 aeroplane equipped with Basic MLG was rolling out after
landing when it experienced a nose wheel steering fault (unrelated
to the safety subject addressed by this AD), which resulted in the
crew stopping the aeroplane on the taxiway after vacating the
runway. The subsequent investigation revealed that the right-hand
MLG sidestay upper cardan pin had migrated out of position. The
sidestay upper cardan nut and retainer had detached from the upper
cardan pin and were found, still bolted together, in the landing
gear bay.
    Prompted by these findings, Airbus published Alert Operators
Transmission (AOT) A32L003-14, providing inspection instructions
and, as an interim solution, EASA issued AD 2014-0066 [which
corresponds to FAA AD 2015-10-03, Amendment 39-18158 (80 FR 30608,
May 29, 2015)] to require repetitive detailed inspections (DET) of
the MLG upper cardan pin, nut and retainer. That AD also required
accomplishment of a one-time gap check between wing rear spar
fitting lugs and the bush flanges and, depending on findings,
corrective action(s). The gap check (including corrections, as
necessary) terminated the repetitive DET.
    Since that [EASA] AD was issued, further investigation concluded
that the reported MLG sidestay upper cardan pin migration event had
been caused by corrosion, due to lack of jointing compound and
inadequate sealant application during MLG installation. Therefore,
this issue affects any MLG that had an upper cardan pin replacement
or re-installation, irrespective of MLG overhaul. Any corrosion on
the upper cardan pin and nut threads would not have been detected
during the previously required DET.
    This condition, if not detected and corrected, could lead to a
complete migration of the sidestay upper cardan pin and a
disconnection of the sidestay upper arm from the aeroplane
structure, possibly resulting in MLG collapse with consequent damage
to the aeroplane and injury to occupants.
    To address this potential unsafe condition, Airbus published
Service Bulletin (SB) A330-32-3269, SB A340-32-4301 and SB A340-32-
5115 providing inspection instructions. In addition, to prevent any
improper re-installation of an upper cardan pin on a MLG, Airbus
amended the applicable Aircraft Maintenance Manual (AMM) on 01
October 2014.
    For the reasons described above, this [EASA] AD supersedes EASA
[AD] 2014-0066 and requires a one-time DET of the MLG upper cardan
pin and nut threads to check for corrosion or damage on the upper
cardan pin and nut threads, and, depending on findings, replacement
of the damaged part(s).
    As this unsafe condition could also develop on A330 freighters
and A340-500/-600 aeroplanes, this [EASA] AD also applies to those
aeroplanes.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0459.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A330-32-3269, dated February 17,
2015.
     Airbus Service Bulletin A340-32-4301, dated February 17,
2015.
     Airbus Service Bulletin A340-32-5115, dated February 17,
2015.
    The service information describes procedures for a detailed
inspection of the upper cardan pin and nut threads for any corrosion,
pitting, or thread damage, and replacement of the cardan pin and nut
threads. This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

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 these
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 95 airplanes of U.S.
registry.
    We also estimate that it would take about 11 work-hours per product
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 this proposed AD on U.S. operators to be $88,825, or $935
per product.
    In addition, we estimate that any necessary follow-on actions would
take about 12 work-hours and require parts costing $78,136, for a cost
of $79,156 per product. We have no way of determining the number of
aircraft that might need this action.

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.

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

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 removing Airworthiness Directive (AD)
2015-10-03, Amendment 39-18158 (80 FR 30608, May 29, 2015), and adding
the following new AD:

Airbus: Docket No. FAA-2016-0459; Directorate Identifier 2015-NM-
081-AD.

(a) Comments Due Date

    We must receive comments by March 7, 2016.

(b) Affected ADs

    This AD replaces 2015-10-03, Amendment 39-18158 (80 FR 30608,
May 29, 2015).

(c) Applicability

    This AD applies to the airplanes, certificated in any category,
identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD,
except airplanes on which an upper cardan pin on a main landing gear
(MLG) has never been replaced or reinstalled since first entry into
service of the airplane.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes,
all manufacturer serial numbers .
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes, all manufacturer serial numbers.
    (3) Airbus Model A340-541 and -642 airplanes, all manufacturer
serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing
Gear.

(e) Reason

    This AD was prompted by a report that an MLG sidestay upper
cardan pin migration event had been caused by corrosion due to lack
of jointing compound and inadequate sealant application during the
MLG installation. We are issuing this AD to detect and correct
migration of the sidestay upper cardan pin, which could result in
disconnection of the sidestay upper arm from the airplane structure,
and could result in a landing gear collapse and consequent damage to
the airplane and injury to occupants.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Definition

    For the purpose of this AD, an upper cardan pin on a MLG is
affected if it has been installed as a replacement part, or
reinstalled since first entry of the airplane into service, and if
the installation was accomplished using the applicable airplane
maintenance manual at a revision level prior to October 1, 2014.

(h) Inspection and Replacement

    (1) For an affected upper cardan pin on an MLG: Before exceeding
96 months since its latest installation on an airplane, or within 12
months after the effective date of this AD, whichever occurs later,
do a detailed inspection of the upper cardan pin and nut threads for
any corrosion, pitting, or thread damage, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraph (i) of this AD.
    (2) If, during the detailed inspection specified in paragraph
(h)(1) of this AD, any corrosion, pitting, or thread damage is
found, before further flight, replace the upper cardan pin and/or
nut, as applicable, in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraph (i) of this AD.

(i) Applicable Service Information

    Do the actions required by paragraph (h) of this AD in
accordance with the Accomplishment Instructions of the applicable
service information identified in paragraphs (i)(1), (i)(2), and
(i)(3) of this AD.
    (1) Airbus Service Bulletin A330-32-3269, dated February 17,
2015 (for Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes).
    (2) Airbus Service Bulletin A340-32-4301, dated February 17,
2015 (for Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes).
    (3) Airbus Service Bulletin A340-32-5115, dated February 17,
2015 (for Airbus Model A340-541 and -642 airplanes).

(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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM 116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>. Information
may be emailed to<EMAIL_ADDRESS>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) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0079, dated May 7, 2015,
for related information. This MCAI may be found in the AD docket on
the Internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2016-0459.
    (2) For service information identified in this 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<EMAIL_ADDRESS>
Internet http://www.airbus.com. You may view this 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<PHONE_NUMBER>.

    Issued in Renton, Washington, on January 8, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-00944 Filed 1-20-16; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register: October 5, 2007 (Volume 72, Number 193)]
[Rules and Regulations]
[Page 56890-56891]
[DOCID:fr05oc07-3]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26491 Directorate Identifier 2006-CE-076-AD;
Amendment 39-15218; AD 2007-20-08]
RIN 2120-AA64

Airworthiness Directives; Alpha Aviation Design Limited (Type
Certificate No. A48EU Previously Held by Apex Aircraft and Avions
Pierre Robin) Model R2160 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) issued 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:

    To prevent fuel system leaks inspect the bronze/brass hollow
threaded fuel line fittings for type and leaks, per Avions Pierre
Robin Service Bulletin (SB) No. 86.

We are issuing this AD to require actions to correct the unsafe
condition on these products.

DATES: This AD becomes effective November 9, 2007.
    On November 9, 2007, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in this
AD.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov
 or in person at Document Management Facility, U.S.

Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC
20590.

FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (NPRM) to
amend 14 CFR part 39 to include an AD that would apply to the specified
products. That supplemental NPRM was published in the Federal Register
on August 13, 2007 (72 FR 45183). That supplemental NPRM proposed to
correct an unsafe condition for the specified products. The MCAI
states:

    To prevent fuel system leaks inspect the bronze/brass hollow
threaded fuel line fittings for type and leaks, per Avions Pierre
Robin Service Bulletin (SB) No. 86. Replace leaking Type 1 fuel line
fittings with Type 2 fittings, per SB No. 86, before further flight.

    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 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.

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 FAA policies. Any such differences are
highlighted in a Note within the AD.

Costs of Compliance

    We estimate that this AD will affect about 10 products of U.S.
registry. We also estimate that it will take about 1 work-hour 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 $100
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 costs. 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 on U.S.
operators to be $1,800, or $180 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 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://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 the NPRM, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (telephone<PHONE_NUMBER>) 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:

2007-20-08 Alpha Aviation Design Limited (Type Certificate No. A48EU
previously held by Apex Aircraft and Avions Pierre Robin): Amendment
39-15218; Docket No. FAA-2006-26491; Directorate Identifier 2006-CE-
076-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November
9, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model R2160 airplanes, serial numbers 001
through 191, certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 28: Fuel.

Reason

    (e) The mandatory continuing airworthiness information (MCAI)
states:
    To prevent fuel system leaks inspect the bronze/brass hollow
threaded fuel line fittings for type and leaks, per Avions Pierre
Robin Service Bulletin (SB) No. 86.

Actions and Compliance

    (f) Unless already done, within the next 25 hours time-in-
service after November 9, 2007 (the effective date of this AD)
replace the Type 1 fuel line fittings with Type 2 fittings following
Avions Pierre Robin Service Bulletin No. 86, dated July, 1980.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information
as follows: This AD requires the replacement of the Type 1 fuel line
fittings with Type 2 fittings following Avions Pierre Robin Service
Bulletin No. 86, dated July, 1980. The MCAI required a one-time
inspection for leaks and replacement if leaks were found. There was
no MCAI action to determine whether leaks developed in the future.
The FAA believes that mandatory replacement of the fittings will
eliminate current leaking fittings as well as preventing the problem
from developing in the future.

 Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, 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: Karl Schletzbaum, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
    (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 Airworthiness Authority of New Zealand AD DCA/
R2000/12, dated June 29, 2006, and Avions Pierre Robin Service
Bulletin No. 86, dated July, 1980, for related information.

Material Incorporated by Reference

    (i) You must use Avions Pierre Robin Service Bulletin No. 86,
dated July, 1980, 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 Alpha
Aviation Design Ltd., Ingram Road, Hamilton Airport, R.D.2. Hamilton
3282, New Zealand.
    (3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri
64106; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html
.

    Issued in Kansas City, Missouri, on September 27, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-19501 Filed 10-4-07; 8:45 am]

BILLING CODE 4910-13-P