Airworthiness Directives; Airbus Airplanes, 25936-25940 [2017-11129]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 82, Number 107 (Tuesday, June 6, 2017)]
[Rules and Regulations]
[Pages 25936-25940]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-11129]



[[Page 25936]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8182; Directorate Identifier 2016-NM-069-AD; 
Amendment 39-18906; AD 2017-11-07]
RIN 2120-AA64


Airworthiness Directives; Airbus 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 all 
Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -
114, and -115 airplanes; Model A320-211, -212, and -214 airplanes; and 
Model A321-111, -112, -211, -212, and -213 airplanes. This AD was 
prompted by reports of cracks in certain pivot fittings of a CFM56 
engine's thrust reverser (T/R). This AD requires repetitive inspections 
for cracking and corrosion of certain pivot fittings of a CFM56 
engine's T/R, and corrective actions if necessary. We are issuing this 
AD to address the unsafe condition on these products.

DATES: This AD is effective July 11, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of July 11, 
2017.

ADDRESSES: For Airbus service information identified in this final 
rule, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet 
https://www.airbus.com.
    For Goodrich Aerostructures service information identified in this 
final rule, contact Goodrich Aerostructures, 850 Lagoon Drive, Chula 
Vista, CA 91910-2098; telephone 619-691-2719; email 
jan.lewis@goodrich.com; Internet https://techpubs.goodrich.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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8182.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8182; 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 
800-647-5527) is Docket 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A318-111 
and -112 airplanes; Model A319-111, -112, -113, -114, and -115 
airplanes; Model A320-211, -212, and -214 airplanes; and Model A321-
111, -112, -211, -212, and -213 airplanes. The NPRM published in the 
Federal Register on August 3, 2016 (81 FR 51142). The NPRM was prompted 
by reports of cracks on the 3 o'clock and 9 o'clock pivot fittings of a 
CFM56 engine's T/R. The NPRM proposed to require repetitive inspections 
for cracking and corrosion of the 3 o'clock and 9 o'clock pivot 
fittings of a CFM56 engine's T/R, and corrective actions if necessary. 
We are issuing this AD to detect and correct such cracking and 
corrosion, which could lead to T/R malfunction and, in a case of 
rejected takeoff at V1 on a wet runway, a consequent runway 
excursion, possibly resulting in damage to the airplane and injury to 
occupants.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0076, dated April 18, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 
airplanes; Model A320-211, -212, and -214 airplanes; and Model A321-
111, -112, -211, -212, and -213 airplanes. The MCAI states:

    Several operators reported finding cracks, during an unscheduled 
inspection, on the 3 o'clock and 9 o'clock pivot fittings of a CFM56 
engine's thrust reverser (T/R). Investigation results revealed that 
these cracks were caused by a combination of stress and fatigue 
effects. Further analysis determined that only aeroplanes fitted 
with CFM56-5A or CFM56-5B series engines could be affected by this 
issue.
    This condition, if not detected and corrected, could lead to T/R 
malfunction and, in a case of rejected take off at V1 on a wet 
runway, a consequent runway excursion, possibly resulting in damage 
to the aeroplane and injury to occupants.
    For the reasons described above, EASA issued AD 2016-0068, 
requiring repetitive inspections [for cracks and corrosion] of the 
T/R pivot fittings at the 3 o'clock and 9 o'clock positions and, 
depending on findings, accomplishment of applicable corrective 
action(s).
    Since that [EASA] AD was issued, it was determined that the list 
of part numbers (P/N) of affected T/R pivot fitting, as identified 
in that [EASA] AD, was incomplete.
    For the reason stated above, this [EASA] AD retains the 
requirements of EASA AD 2016-0068, which is superseded, but expands 
the list of affected fitting P/Ns.

    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8182.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Revise Repetitive Inspection Interval

    American Airlines (AA) requested that we revise paragraph (g) of 
the proposed AD to change the proposed repetitive inspection interval 
for inspecting the T/R pivot fittings from 60 months to 10 years to 
match certain airworthiness limitation items (ALIs). AA stated that 
aligning the inspection interval with existing ALIs allows 
accomplishment of the inspection during a shop overhaul along with 
other ALIs. AA stated that this will significantly reduce the burden on 
operators. AA explained that changing this compliance time will not 
affect the likelihood of fatigue cracking, since fatigue effects are 
cycle-based and the same cycle-threshold is maintained.
    We do not agree with AA's request. EASA, as the State of Design 
Authority for Airbus products, has determined

[[Page 25937]]

that the compliance time of 60 months represents the maximum interval 
of time allowable for the affected airplanes to continue to safely 
operate. This determination is based on the severity of the failure and 
the likelihood of the failure's occurrence, and takes into account the 
overall risk to the fleet. The FAA and EASA worked with Airbus to 
ensure that all appropriate actions are taken at the appropriate times 
to mitigate risk to the fleet. However, under the provisions of 
paragraph (l)(1) of this AD, we will consider requests for approval of 
a revised inspection interval if sufficient data are submitted to 
substantiate that the inspection interval would provide an acceptable 
level of safety. We have not changed this AD in this regard.

Request To Use Later Revisions of Service Information

    AA requested that we allow the use of later revisions of the 
service information for accomplishment of the actions specified in 
paragraph (g) of the proposed AD. AA asserted that future revisions of 
the referenced service information will have additional analysis and 
insight into the design and failure modes of the structure. 
Additionally, AA pointed out that the FAA will have an opportunity to 
object to any revisions the manufacturer proposes.
    We do not agree with AA's request. We may not refer to any document 
in an AD that does not yet exist.
    In general terms, we are required by the Office of the Federal 
Register (OFR) regulations to either publish the service document 
contents as part of the actual AD language; or submit the service 
document to the OFR for approval as ``referenced'' material, in which 
case we may only refer to such material in the text of an AD. The AD 
may refer to the service document only if the OFR approved it for 
``incorporation by reference.'' See 1 CFR part 51.
    To allow operators to use later revisions of the referenced 
document (issued after publication of the AD), either we must revise 
the AD to reference specific later revisions, or operators must request 
approval to use later revisions as an alternative method of compliance 
with this AD under the provisions of paragraph (l)(1) of this AD. We 
have not changed this AD in this regard.

Request To Revise Service Information Date

    AA requested that we revise the ``Related Service Information under 
1 CFR part 51'' section of the preamble and paragraphs (g) and (j) of 
the proposed AD to correct the revision date specified for Airbus 
Service Bulletin A320-70-1003, Revision 01, dated December 28, 2015. AA 
pointed out that in the NPRM the release date is stated as December 18, 
2015, instead of December 28, 2015.
    We agree to fix the typographical error. We have revised this final 
rule accordingly.

Request To Clarify Which Service Information Is Required for Certain 
Actions

    AA requested that we revise paragraphs (g) and (h) of the proposed 
AD to clarify that doing the actions in paragraph (g) of the proposed 
AD in the shop/off-wing requires only accomplishment of Goodrich 
Aerostructures Service Bulletin RA32078-137, Rev. 3, dated March 14, 
2016. AA asserted that the actions specified in Airbus Service Bulletin 
A320-70-1003, Revision 01, dated December 28, 2015, which provides 
open-up instructions for on-wing actions, are not necessary to comply 
with the proposed requirements.
    We do not agree with AA's request to revise paragraphs (g) and (h) 
of this AD to clarify the required actions. However, we do agree to 
clarify the use of the phrase ``as applicable'' in paragraph (g) of 
this AD. The intent of using the phrase ``as applicable'' in paragraph 
(g) of this AD is not to authorize an operator to accomplish either 
Airbus Service Bulletin A320-70-1003, Revision 01, dated December 28, 
2015; or Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 3, 
dated March 14, 2016. Operators must accomplish the actions in 
accordance with the applicable requirements in the Airbus service 
bulletin and the Goodrich Aerostructures service bulletin.
    Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 3, dated 
March 14, 2016, contains more detailed procedures for accomplishing 
certain required actions that are specified in Airbus Service Bulletin 
A320-70-1003, Revision 01, dated December 28, 2015. Therefore, 
operators must use both service bulletins to accomplish the AD 
requirements.
    We also note that Airbus Service Bulletin A320-70-1003, Revision 
01, dated December 28, 2015, contains Required for Compliance (RC) 
actions and specifies only paragraphs 3.C. and 3.D. are RC procedures. 
The ``open-up instructions'' in paragraph 3.B. of the Airbus service 
bulletin are not RC procedures. Those procedures and tests that are not 
identified as RC may be deviated from using accepted methods in 
accordance with the operator's maintenance or inspection program 
without obtaining approval of an alternative method of compliance 
(AMOC), provided the procedures and tests identified as RC can be done 
and the airplane can be put back in an airworthy condition. We have not 
changed this AD in this regard.
    AA also requested that we revise paragraphs (k)(2)(i), (k)(2)(ii), 
and (k)(2)(iii) of the proposed AD to permit the use of any of the 
specified service information by adding the phrase ``as applicable'' 
following references to the service information. AA asserted that this 
revision would prevent any confusion regarding off-wing maintenance for 
which Airbus Service Bulletin A320-70-1003, Revision 01, dated December 
28, 2015, will not be needed since the T/R is not installed on an 
airplane. AA stated that this revision would align the wording in 
paragraph (k) of the proposed AD with the wording in the first sentence 
of paragraph (g) of the proposed AD.
    We do not agree to add ``as applicable'' to paragraphs (k)(2)(i), 
(k)(2)(ii), and (k)(2)(iii) of this AD. If an operator wants to install 
a spare part, then they still need to perform Airbus Service Bulletin 
A320-70-1003, Revision 01, dated December 28, 2015; and Goodrich 
Aerostructures Service Bulletin RA32078-137, Rev. 3, dated March 14, 
2016. For example, if a spare met the 60-month threshold to qualify as 
serviceable then operators are still required to perform the 
operational test of the thrust reversers after installation of the 
fittings. We have not changed this AD in this regard.

Request To Clarify Compliance Time in Paragraph (h)(2) of the Proposed 
AD

    AA requested that we revise paragraph (h)(2) of the proposed AD to 
clarify that the compliance time of 7,200 flight cycles accumulated 
applies to the T/R and not to the airplane.
    We agree that clarification is necessary. The accumulated flight 
cycles are on the T/R, not the airplane. We have revised paragraph 
(h)(2) of this AD accordingly.

Request To Revise or Remove Parts Limitation Compliance Time

    AA requested that we revise paragraph (j) of the proposed AD to 
remove the limitation of fixing the unsafe condition on T/Rs prior to 
installation, as of the effective date of this AD. Rather, AA requested 
that we revise the compliance times to those in paragraph (h) of the 
proposed AD if it is determined that, prior to installation, the T/R 
was removed as part of an

[[Page 25938]]

unrelated on-wing maintenance action. AA stated that paragraph (j) of 
the proposed AD puts a burden on operators to fix the unsafe condition 
on the T/R if the discrepant T/R is removed for any maintenance reason. 
Additionally, AA asserted that the proposed actions require special 
inspection equipment, inventory, consumable materials, etc., which are 
not readily available at all stations, in addition to the necessary 
labor and extensive downtime. Alternatively, AA stated that removal of 
paragraph (j) of the proposed AD would be acceptable.
    We do not agree with AA's request. Paragraph (j) of this AD does 
not require immediate corrective action for a T/R that is removed for 
any maintenance action, unless the T/R exceeds the thresholds specified 
in paragraph (j) of this AD. EASA has determined that the compliance 
time specified in paragraph (j) of this AD should be based on the 
severity of the failure, the likelihood of the failure's occurrence, 
and the overall safety risk to the fleet. The FAA and EASA worked with 
Airbus to ensure that all appropriate action(s) are taken at 
appropriate times to mitigate risk to the fleet. This determination 
took into consideration parts and special tool availability, and 
planning for accomplishment of any necessary corrective action. Airbus 
did not provide us any information related to a short supply of parts 
or tools required for accomplishment of this AD. In addition, it is the 
operator's responsibility to plan appropriately for actions to be taken 
to assure parts and equipment are available for AD compliance. 
Therefore, the FAA's expectation is that, as of the effective date of 
this AD, operators will not install a known unsafe part as specified in 
paragraph (j) of this AD. However, if the part is already installed and 
in-service, then operators may utilize the full compliance time as 
allowed by this AD. Operators have the option of proposing an 
alternative compliance time, with supportive data, in accordance with 
paragraph (l)(1) of this AD. We have not changed this AD in this 
regard.

Request To Permit Flights With Deactivated T/Rs

    AA requested that we revise the proposed AD to allow a minimum 
equipment list (MEL) provision to deactivate affected T/Rs for the 
allowable duration of that MEL item before accomplishing the corrective 
actions specified in the proposed AD. AA explained that this action 
would provide an equivalent level of safety since, during application 
of the MEL, the T/Rs are deactivated and there is never a possibility 
of T/R structural failure due to cracking.
    We agree with AA's request. We have added paragraph (i)(3) to this 
AD to state that it is permissible to dispatch an airplane equipped 
with a T/R pivot fitting(s) having a part number specified in paragraph 
(g)(1) or (g)(2) of this AD, provided the limitations in Master Minimum 
Equipment List Item 78-30-01 (which provides for deactivation of the 
affected T/R) have been followed.

Request To Provide a Provision for Special Flight Permits

    AA requested that the proposed AD be revised to include an 
allowance for special flight permits to allow the operator to operate 
the airplane to a location where the requirements of the proposed AD 
can be accomplished.
    We acknowledge the potential need for a one-time ferry flight. 
Although not specifically stated in the proposed AD, there is no 
restriction prohibiting or limiting special flight permits, as 
described in Section 21.197 and Section 21.199 of the Code of Federal 
Regulations (14 CFR 21.197 and 21.199). Therefore, we have not changed 
this AD regarding this issue.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-70-1003, Revision 01, dated 
December 28, 2015. This service information describes procedures for 
doing inspections for cracking and corrosion of the 3 o'clock and 9 
o'clock pivot fittings of a CFM56 engine's T/R.
    Goodrich Aerostructures has issued Service Bulletin RA32078-137, 
Rev. 3, dated March 14, 2016. This service information describes 
procedures for doing inspections for cracking and corrosion of the 3 
o'clock and 9 o'clock pivot fittings of a CFM56 engine's T/R, and 
repair of corrosion.
    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.

Costs of Compliance

    We estimate that this AD affects 400 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................  4 work-hours x $85             $0  $340 per inspection   $136,000 per
                                    per hour = $340 per                cycle.                inspection cycle.
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions specified in 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

[[Page 25939]]

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.

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 airworthiness 
directive (AD):

2017-11-07 Airbus: Amendment 39-18906; Docket No. FAA-2016-8182; 
Directorate Identifier 2016-NM-069-AD.

(a) Effective Date

    This AD is effective July 11, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) through (c)(4) of this AD, 
all manufacturer serial numbers.
    (1) Airbus Model A318-111 and -112 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, and -115 airplanes.
    (3) Airbus Model A320-211, -212, and -214 airplanes.
    (4) Airbus Model A321-111, -112, -211, -212, and -213 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine 
exhaust.

(e) Reason

    This AD was prompted by reports of cracks on the 3 o'clock and 9 
o'clock pivot fittings of a CFM56 engine's thrust reverser (T/R). We 
are issuing this AD to detect and correct such cracking and 
corrosion, which could lead to T/R malfunction and, in a case of 
rejected takeoff at V1 on a wet runway, a consequent 
runway excursion, possibly resulting in damage to the airplane and 
injury to occupants.

(f) Compliance

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

(g) Inspections and Corrective Actions

    At the applicable compliance time specified in paragraph (h) of 
this AD: Do a high frequency eddy current (HFEC) inspection for 
cracking and corrosion of each T/R pivot fitting specified in 
paragraphs (g)(1) and (g)(2) of this AD, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-70-1003, Revision 01, 
dated December 28, 2015; and Goodrich Aerostructures Service 
Bulletin RA32078-137, Rev. 3, dated March 14, 2016; as applicable; 
except as required by paragraph (i) of this AD. Do all applicable 
corrective actions before further flight. Repeat the inspection of 
the T/R pivot fittings thereafter at intervals not to exceed 60 
months or 12,000 flight cycles, whichever occurs first.
    (1) The 3 o'clock position T/R pivot fittings having part 
numbers (P/N) that are provided in paragraphs (g)(1)(i) through 
(g)(1)(iv) of this AD.
    (i) P/N 321-200-850-6.
    (ii) P/N 321-200-851-6.
    (iii) P/N 321-200-852-6.
    (iv) P/N 321-200-853-6.
    (2) The 9 o'clock position T/R pivot fittings having P/Ns that 
are provided in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD.
    (i) P/N 321-200-800-6.
    (ii) P/N 321-200-801-6.
    (iii) P/N 321-200-802-6.
    (iv) P/N 321-200-803-6.

(h) Compliance Times

    At the later of the times specified in paragraphs (h)(1) and 
(h)(2) of this AD, do the initial inspection specified in paragraph 
(g) of this AD. If maintenance records cannot conclusively determine 
the T/R flight cycles accumulated since first installation, or the 
time since new, do the initial inspection required by paragraph (g) 
of this AD at the compliance time specified in paragraph (h)(2) of 
this AD.
    (1) Before exceeding 10 years or 24,000 total flight cycles 
accumulated by the T/R, whichever occurs first since first 
installation on an airplane.
    (2) Within 36 months or 7,200 flight cycles accumulated by the 
T/R, whichever occurs first after the effective date of this AD.

(i) Exceptions to Service Information Specifications

    (1) If any crack is found during any inspection required by this 
AD: Before further flight, repair 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).
    (2) If any corrosion is found during any inspection required by 
this AD and Goodrich Aerostructures Service Bulletin RA32078-137, 
Rev. 3, dated March 14, 2016, specifies obtaining a damage 
disposition from Goodrich Aerostructures: Before further flight, 
repair using a method approved by the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the EASA; or 
Airbus's EASA DOA.
    (3) Dispatch of an airplane equipped with a T/R pivot fitting(s) 
having a part number identified in paragraph (g)(1) or (g)(2) of 
this AD, as specified in Master Minimum Equipment List (MMEL) 78-30-
01 (deactivation of the affected T/Rs), is permitted provided the 
limitations specified in MMEL 78-30-01 have been followed.

(j) Parts Installation Limitation

    As of the effective date of this AD, no person may install on 
any airplane a T/R pivot fitting having a part number specified in 
paragraph (g)(1) or (g)(2) of this AD, unless it is determined, 
prior to installation, that the T/R pivot fitting has accumulated 
less than 10 years and fewer than 24,000 total flight cycles since 
its first installation on an airplane, or less than 60 months and 
fewer than 12,000 flight cycles after having passed an inspection, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-70-1003, Revision 01, dated December 28, 2015; and 
Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 3, dated 
March 14, 2016.

(k) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-70-
1003, dated May 7, 2014.
    (2) This paragraph provides credit for actions specified in 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using the service information specified in 
paragraph (k)(2)(i), (k)(2)(ii), or (k)(2)(iii) of this AD.
    (i) Airbus Service Bulletin A320-70-1003, dated May 7, 2014; and 
Goodrich Aerostructures Service Bulletin RA32078-137, dated April 
29, 2014.
    (ii) Airbus Service Bulletin A320-70-1003, dated May 7, 2014; 
and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 1, 
dated January 26, 2015.
    (iii) Airbus Service Bulletin A320-70-1003, dated May 7, 2014; 
and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 2, 
dated December 2, 2015.

[[Page 25940]]

(l) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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.
    (2) Contacting the Manufacturer: 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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (i) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0076, dated April 18, 2016, 
for related information. This MCAI may be found in the AD docket on 
the Internet at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-8182.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3), (n)(4), and (n)(5) of this AD.

(n) 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 this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-70-1003, Revision 01, dated 
December 28, 2015.
    (ii) Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 
3, dated March 14, 2016.
    (3) For Airbus service information identified in this AD, 
contact Airbus service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
    (4) For Goodrich Aerostructures service information identified 
in this AD, contact Goodrich Aerostructures, 850 Lagoon Drive, Chula 
Vista, CA 91910-2098; telephone 619-691-2719; email 
jan.lewis@goodrich.com; Internet https://techpubs.goodrich.com.
    (5) 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 
425-227-1221.
    (6) You may view this 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-11129 Filed 6-5-17; 8:45 am]
 BILLING CODE 4910-13-P