81 FR 26113 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 84 (May 2, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 84 (May 2, 2016)
| Page Range | 26113-26115 | |
| FR Document | 2016-10117 |
[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)] [Rules and Regulations] [Pages 26113-26115] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-10117] [[Page 26113]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-6539; Directorate Identifier 2015-NM-036-AD; Amendment 39-18504; AD 2016-09-06] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) 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 the results of an evaluation by the design approval holder (DAH). During a residual fatigue test, the forward engine mount failed prior to reaching the threshold/interval for the detailed inspections of the forward engine mounts specified in the airworthiness limitations. This AD requires repetitive detailed inspections of the right and left forward engine mounts, and corrective action if necessary. These inspections are required by AD 2015-05-02. This AD reduces the compliance times for those inspections. We are issuing this AD to detect and correct fatigue cracking in the forward engine mounts. Such cracking could result in reduced structural integrity of the airplane and could lead to in-flight loss of an engine, possibly resulting in reduced controllability of the airplane. DATES: This AD is effective June 6, 2016. ADDRESSES: For 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 [email protected]; 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-2015- 6539; 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 November 30, 2015 (80 FR 74723) (``the NPRM''). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0038, dated March 4, 2015 (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: During a A320 Extended Service Goal (ESG) residual fatigue test, in which new loads were used, taking into account the results of the 2006 fleet survey, the CFM56-5A/5B forward engine mount experienced a failure before reaching the threshold/interval for the detailed inspection of that forward engine mount, as identified in Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 2 (hereafter referred to in this [EASA] AD as `the ALS') task 712111- 01. In case of total loss of the primary load path, the current maintenance requirements do not ensure the design integrity of the remaining structure. This condition, if not corrected, could lead to in-flight loss of an engine, possibly resulting in reduced control of the aeroplane and injury to persons on the ground. For the reasons described above, this [EASA] AD requires implementation of a reduced threshold and interval for the detailed inspections (DET) of the forward engine mount on both right hand (RH) and left hand (LH) sides, as specified in the ALS, task 712111- 01. Once further investigations and test are completed, the threshold and interval of the ALS task 712111-01 will likely be modified accordingly. Required actions include repair of discrepancies (cracks) found during the inspection. 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-2015-6539. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA's response. Request To Clarify That This Final Rule Was Not Prompted by Widespread Fatigue Damage (WFD) Airbus requested that all references to WFD be removed from the NPRM. Airbus stated that the root cause of the unsafe condition was not associated with WFD. The unsafe condition was revealed during a residual fatigue test of the CFM56-5A/5B forward engine mount. The forward engine mount failed prior to reaching the threshold/interval for the detailed inspections specified in the Airbus A318/A319/A320/ A321 Airworthiness Limitations Section Part 2--Damage-Tolerant Airworthiness Limitation Items. Based on the information provided by the commenter we agree to remove all references to WFD from the preamble and regulatory text and include an explanation that this final rule was prompted by the results of an evaluation by the DAH. Conclusion We reviewed the relevant data, considered the comment 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. [[Page 26114]] Costs of Compliance We estimate that this AD affects 940 airplanes 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 $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $79,900, or $85 per product. We have received no definitive data that will enable us to provide cost estimates for the on-condition parts cost 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 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): 2016-09-06 Airbus: Amendment 39-18504. Docket No. FAA-2015-6539; Directorate Identifier 2015-NM-036-AD. (a) Effective Date This AD is effective June 6, 2016. (b) Affected AD This AD affects AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015) (``AD 2015-05-02''). (c) Applicability This AD applies to all Airbus airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD. (1) Model A318-111 and -112 airplanes. (2) Model A319-111, -112, -113, -114, and -115 airplanes. (3) Model A320-211, -212, and -214 airplanes. (4) Model A321-111, -112, -211, -212, and -213 airplanes. (d) Subject Air Transport Association (ATA) of America Code 05, Periodic Inspections. (e) Reason This AD was prompted by the results of an evaluation by the design approval holder. During a residual fatigue test the forward engine mount failed prior to reaching the threshold/interval for the detailed inspections of the forward engine mounts specified in the airworthiness limitations. We are issuing this AD to detect and correct fatigue cracking in the forward engine mounts. Such cracking could result in reduced structural integrity of the airplane and could lead to in-flight loss of an engine, possibly resulting in reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections At the latest of the times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Do a detailed inspection of the left and right forward engine mounts for discrepancies (cracking), using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Repeat the inspection thereafter at intervals not to exceed 800 flight cycles. Note 1 to paragraphs (g) and (h) of this AD: Guidance for the inspection and engine mount replacement can be found in Task 712111- 210-040 of the Airbus A318/A319/A320/A321 Maintenance Manual. (1) Within 800 flight cycles since the first flight of the airplane. (2) Within 800 flight cycles since the most recent detailed inspection specified in Airbus Airworthiness Limitation Tasks 712111-01-1, 712111-01-2, 712111-01-3, or 712111-01-4, ``Detailed Inspection of Forward Engine Mount Installation,'' as applicable. (3) Within 800 flight cycles after the effective date of this AD. (h) Corrective Action If any discrepancy (cracking) is found during any inspection required by paragraph (g) of this AD: Before further flight, replace the affected forward engine mount with a serviceable part, 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). (i) No Terminating Action Replacement of a forward engine mount does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD. (j) Termination of Certain Tasks Required by AD 2015-05-02 Accomplishment of the inspections required by paragraph (g) of this AD terminates the initial and repetitive inspections specified in paragraph (n)(2) of AD 2015-05-02, for Airbus Airworthiness Limitation Tasks 712111-01-1, 712111-01-2, 712111-01-3, and 712111- 01-4, ``Detailed Inspection of Forward Engine Mount Installation.'' (k) 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- [[Page 26115]] [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) 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 the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (l) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0038, dated March 4, 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-2015-6539. (2) For 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 [email protected]; 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 425-227-1221. (n) Material Incorporated by Reference None. Issued in Renton, Washington, on April 20, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-10117 Filed 4-29-16; 8:45 am] BILLING CODE 4910-13-P
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DEPARTMENT OF TRANSPORTATION 6539; or in person at the Docket For the reasons described above, this
Management Facility between 9 a.m. [EASA] AD requires implementation of a
Federal Aviation Administration and 5 p.m., Monday through Friday, reduced threshold and interval for the
detailed inspections (DET) of the forward
except Federal holidays. The AD docket
engine mount on both right hand (RH) and
14 CFR Part 39 contains this AD, the regulatory left hand (LH) sides, as specified in the ALS,
[Docket No. FAA–2015–6539; Directorate evaluation, any comments received, and task 712111–01.
Identifier 2015–NM–036–AD; Amendment other information. The street address for Once further investigations and test are
39–18504; AD 2016–09–06] the Docket Office (telephone 800–647– completed, the threshold and interval of the
5527) is Docket Management Facility, ALS task 712111–01 will likely be modified
RIN 2120–AA64 accordingly.
U.S. Department of Transportation,
Airworthiness Directives; Airbus Docket Operations, M–30, West Required actions include repair of
Airplanes Building Ground Floor, Room W12–140, discrepancies (cracks) found during the
1200 New Jersey Avenue SE., inspection. You may examine the MCAI
AGENCY: Federal Aviation Washington, DC 20590. in the AD docket on the Internet at
Administration (FAA), Department of FOR FURTHER INFORMATION CONTACT: http://www.regulations.gov by searching
Transportation (DOT). Sanjay Ralhan, Aerospace Engineer, for and locating Docket No. FAA–2015–
ACTION: Final rule. International Branch, ANM–116, 6539.
Transport Airplane Directorate, FAA,
SUMMARY: We are adopting a new 1601 Lind Avenue SW., Renton, WA Comments
airworthiness directive (AD) for all 98057–3356; telephone 425–227–1405; We gave the public the opportunity to
Airbus Model A318–111 and –112 fax 425–227–1149. participate in developing this AD. The
airplanes; Model A319–111, –112, –113, SUPPLEMENTARY INFORMATION: following presents the comment
–114, and –115 airplanes; Model A320– received on the NPRM and the FAA’s
211, –212, and –214 airplanes; and Discussion
response.
Model A321–111, –112, –211, –212, and We issued a notice of proposed
–213 airplanes. This AD was prompted rulemaking (NPRM) to amend 14 CFR Request To Clarify That This Final Rule
by the results of an evaluation by the part 39 by adding an AD that would Was Not Prompted by Widespread
design approval holder (DAH). During a apply to all Airbus Model A318–111 Fatigue Damage (WFD)
residual fatigue test, the forward engine and –112 airplanes; Model A319–111, Airbus requested that all references to
mount failed prior to reaching the –112, –113, –114, and –115 airplanes; WFD be removed from the NPRM.
threshold/interval for the detailed Model A320–211, –212, and –214 Airbus stated that the root cause of the
inspections of the forward engine airplanes; and Model A321–111, –112, unsafe condition was not associated
mounts specified in the airworthiness –211, –212, and –213 airplanes. The with WFD. The unsafe condition was
limitations. This AD requires repetitive NPRM published in the Federal revealed during a residual fatigue test of
detailed inspections of the right and left Register on November 30, 2015 (80 FR the CFM56–5A/5B forward engine
forward engine mounts, and corrective 74723) (‘‘the NPRM’’). mount. The forward engine mount
action if necessary. These inspections The European Aviation Safety Agency failed prior to reaching the threshold/
are required by AD 2015–05–02. This (EASA), which is the Technical Agent interval for the detailed inspections
AD reduces the compliance times for for the Member States of the European specified in the Airbus A318/A319/
those inspections. We are issuing this Union, has issued EASA Airworthiness A320/A321 Airworthiness Limitations
AD to detect and correct fatigue Directive 2015–0038, dated March 4, Section Part 2—Damage-Tolerant
cracking in the forward engine mounts. 2015 (referred to after this as the Airworthiness Limitation Items.
Such cracking could result in reduced Mandatory Continuing Airworthiness Based on the information provided by
structural integrity of the airplane and Information, or ‘‘the MCAI’’), to correct the commenter we agree to remove all
could lead to in-flight loss of an engine, an unsafe condition for all Airbus references to WFD from the preamble
possibly resulting in reduced Model A318–111 and –112 airplanes; and regulatory text and include an
controllability of the airplane. Model A319–111, –112, –113, –114, and explanation that this final rule was
DATES: This AD is effective June 6, 2016. –115 airplanes; Model A320–211, –212, prompted by the results of an evaluation
ADDRESSES: For service information and –214 airplanes; and Model A321– by the DAH.
identified in this final rule, contact 111, –112, –211, –212, and –213
airplanes. The MCAI states: Conclusion
Airbus, Airworthiness Office—EIAS, 1
Rond Point Maurice Bellonte, 31707 During a A320 Extended Service Goal We reviewed the relevant data,
Blagnac Cedex, France; telephone +33 5 (ESG) residual fatigue test, in which new considered the comment received, and
61 93 36 96; fax +33 5 61 93 44 51; email loads were used, taking into account the determined that air safety and the
results of the 2006 fleet survey, the CFM56– public interest require adopting this AD
account.airworth-eas@airbus.com;
5A/5B forward engine mount experienced a with the changes described previously
Internet http://www.airbus.com. You failure before reaching the threshold/interval
may view this referenced service for the detailed inspection of that forward and minor editorial changes. We have
information at the FAA, Transport engine mount, as identified in Airbus A318/ determined that these minor changes:
Airplane Directorate, 1601 Lind Avenue A319/A320/A321 Airworthiness Limitations • Are consistent with the intent that
SW., Renton, WA. For information on Section (ALS) Part 2 (hereafter referred to in was proposed in the NPRM for
the availability of this material at the this [EASA] AD as ‘the ALS’) task 712111– correcting the unsafe condition; and
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FAA, call 425–227–1221. 01. In case of total loss of the primary load • Do not add any additional burden
path, the current maintenance requirements upon the public than was already
Examining the AD Docket do not ensure the design integrity of the
proposed in the NPRM.
remaining structure.
You may examine the AD docket on This condition, if not corrected, could lead We also determined that these
the Internet at http:// to in-flight loss of an engine, possibly changes will not increase the economic
www.regulations.gov by searching for resulting in reduced control of the aeroplane burden on any operator or increase the
and locating Docket No. FAA–2015– and injury to persons on the ground. scope of this AD.
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Costs of Compliance List of Subjects in 14 CFR Part 39 (g) Repetitive Inspections
At the latest of the times specified in
We estimate that this AD affects 940 Air transportation, Aircraft, Aviation paragraphs (g)(1), (g)(2), and (g)(3) of this AD:
airplanes of U.S. registry. safety, Incorporation by reference, Do a detailed inspection of the left and right
We also estimate that it will take Safety. forward engine mounts for discrepancies
about 1 work-hour per product to (cracking), using a method approved by the
Adoption of the Amendment Manager, International Branch, ANM–116,
comply with the basic requirements of
Transport Airplane Directorate, FAA. Repeat
this AD. The average labor rate is $85 Accordingly, under the authority the inspection thereafter at intervals not to
per work-hour. Based on these figures, delegated to me by the Administrator, exceed 800 flight cycles.
we estimate the cost of this AD on U.S. the FAA amends 14 CFR part 39 as Note 1 to paragraphs (g) and (h) of this
operators to be $79,900, or $85 per follows: AD: Guidance for the inspection and engine
product. mount replacement can be found in Task
PART 39—AIRWORTHINESS 712111–210–040 of the Airbus A318/A319/
We have received no definitive data
DIRECTIVES A320/A321 Maintenance Manual.
that will enable us to provide cost
estimates for the on-condition parts cost (1) Within 800 flight cycles since the first
specified in this AD. ■ 1. The authority citation for part 39 flight of the airplane.
continues to read as follows: (2) Within 800 flight cycles since the most
Authority for This Rulemaking recent detailed inspection specified in Airbus
Authority: 49 U.S.C. 106(g), 40113, 44701. Airworthiness Limitation Tasks 712111–01–
Title 49 of the United States Code 1, 712111–01–2, 712111–01–3, or 712111–
specifies the FAA’s authority to issue § 39.13 [Amended] 01–4, ‘‘Detailed Inspection of Forward
rules on aviation safety. Subtitle I, Engine Mount Installation,’’ as applicable.
■ 2. The FAA amends § 39.13 by adding (3) Within 800 flight cycles after the
section 106, describes the authority of
the following new airworthiness effective date of this AD.
the FAA Administrator. ‘‘Subtitle VII:
directive (AD): (h) Corrective Action
Aviation Programs,’’ describes in more
detail the scope of the Agency’s 2016–09–06 Airbus: Amendment 39–18504. If any discrepancy (cracking) is found
authority. Docket No. FAA–2015–6539; Directorate during any inspection required by paragraph
Identifier 2015–NM–036–AD. (g) of this AD: Before further flight, replace
We are issuing this rulemaking under
(a) Effective Date the affected forward engine mount with a
the authority described in ‘‘Subtitle VII, serviceable part, using a method approved by
Part A, Subpart III, Section 44701: This AD is effective June 6, 2016. the Manager, International Branch, ANM–
General requirements.’’ Under that (b) Affected AD 116, Transport Airplane Directorate, FAA; or
section, Congress charges the FAA with the European Aviation Safety Agency
promoting safe flight of civil aircraft in This AD affects AD 2015–05–02, (EASA); or Airbus’s EASA Design
Amendment 39–18112 (80 FR 15152, March Organization Approval (DOA).
air commerce by prescribing regulations 23, 2015) (‘‘AD 2015–05–02’’).
for practices, methods, and procedures (i) No Terminating Action
the Administrator finds necessary for (c) Applicability
Replacement of a forward engine mount
safety in air commerce. This regulation This AD applies to all Airbus airplanes, does not constitute terminating action for the
is within the scope of that authority certificated in any category, identified in repetitive inspections required by paragraph
because it addresses an unsafe condition paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of (g) of this AD.
that is likely to exist or develop on this AD.
(1) Model A318–111 and –112 airplanes. (j) Termination of Certain Tasks Required by
products identified in this rulemaking AD 2015–05–02
(2) Model A319–111, –112, –113, –114, and
action.
–115 airplanes. Accomplishment of the inspections
Regulatory Findings (3) Model A320–211, –212, and –214 required by paragraph (g) of this AD
airplanes. terminates the initial and repetitive
We determined that this AD will not (4) Model A321–111, –112, –211, –212, and inspections specified in paragraph (n)(2) of
have federalism implications under –213 airplanes. AD 2015–05–02, for Airbus Airworthiness
Executive Order 13132. This AD will Limitation Tasks 712111–01–1, 712111–01–
(d) Subject 2, 712111–01–3, and 712111–01–4, ‘‘Detailed
not have a substantial direct effect on
Air Transport Association (ATA) of Inspection of Forward Engine Mount
the States, on the relationship between
America Code 05, Periodic Inspections. Installation.’’
the national government and the States,
or on the distribution of power and (e) Reason (k) Other FAA AD Provisions
responsibilities among the various This AD was prompted by the results of an The following provisions also apply to this
levels of government. evaluation by the design approval holder. AD:
For the reasons discussed above, I During a residual fatigue test the forward (1) Alternative Methods of Compliance
engine mount failed prior to reaching the (AMOCs): The Manager, International
certify that this AD: Branch, ANM–116, Transport Airplane
threshold/interval for the detailed
1. Is not a ‘‘significant regulatory inspections of the forward engine mounts Directorate, FAA, has the authority to
action’’ under Executive Order 12866; specified in the airworthiness limitations. We approve AMOCs for this AD, if requested
2. Is not a ‘‘significant rule’’ under the are issuing this AD to detect and correct using the procedures found in 14 CFR 39.19.
fatigue cracking in the forward engine In accordance with 14 CFR 39.19, send your
DOT Regulatory Policies and Procedures request to your principal inspector or local
mounts. Such cracking could result in
(44 FR 11034, February 26, 1979); reduced structural integrity of the airplane Flight Standards District Office, as
mstockstill on DSK3G9T082PROD with RULES
3. Will not affect intrastate aviation in and could lead to in-flight loss of an engine, appropriate. If sending information directly
Alaska; and possibly resulting in reduced controllability to the International Branch, send it to ATTN:
of the airplane. Sanjay Ralhan, Aerospace Engineer,
4. Will not have a significant International Branch, ANM–116, Transport
economic impact, positive or negative, (f) Compliance Airplane Directorate, FAA, 1601 Lind
on a substantial number of small entities Comply with this AD within the Avenue SW., Renton, WA 98057–3356;
under the criteria of the Regulatory compliance times specified, unless already telephone 425–227–1405; fax 425–227–1149.
Flexibility Act. done. Information may be emailed to: 9–ANM–116–
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AMOC–REQUESTS@faa.gov. Before using ACTION: Final rule. 1601 Lind Avenue SW., Renton, WA
any approved AMOC, notify your appropriate 98057–3356; telephone 425–227–1405;
principal inspector, or lacking a principal SUMMARY: We are adopting a new fax 425–227–1149.
inspector, the manager of the local flight airworthiness directive (AD) for all
standards district office/certificate holding SUPPLEMENTARY INFORMATION:
Airbus Model A318, A319, A320, and
district office. The AMOC approval letter A321 series airplanes. This AD was Discussion
must specifically reference this AD. prompted by reports of in-flight loss of
(2) Contacting the Manufacturer: For any We issued a notice of proposed
fixed and hinged main landing gear rulemaking (NPRM) to amend 14 CFR
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
(MLG) fairings, and reports of post- part 39 by adding an AD that would
be accomplished using a method approved modification MLG fixed fairing apply to all Airbus Model A318, A319,
by the Manager, International Branch, ANM– assemblies that have wear and A320, and A321 series airplanes. The
116, Transport Airplane Directorate, FAA; or corrosion. This AD requires, for certain NPRM published in the Federal
the EASA; or Airbus’s EASA DOA. If airplanes, repetitive replacements of the Register on July 8, 2015 (80 FR 38992)
approved by the DOA, the approval must fixed fairing upper and lower
include the DOA-authorized signature. (‘‘the NPRM’’). The NPRM was
attachment studs of both left-hand (LH) prompted by reports of in-flight loss of
(l) Special Flight Permits and the right-hand (RH) MLG; and fixed and hinged MLG fairings, and
Special flight permits, as described in
repetitive inspections for corrosion, reports of post-modification MLG fixed
Section 21.197 and Section 21.199 of the wear, fatigue cracking, and loose studs fairing assemblies that have wear and
Federal Aviation Regulations (14 CFR 21.197 of each forward stud assembly of the corrosion. The NPRM proposed to
and 21.199), are not allowed. fixed fairing door upper and lower require, for certain airplanes, repetitive
forward attachment of both LH and RH replacements of the fixed fairing upper
(m) Related Information
MLG; and replacement if necessary. and lower attachment studs of both the
(1) Refer to Mandatory Continuing This AD also provides an optional
Airworthiness Information (MCAI) EASA LH and RH MLG; and repetitive
terminating modification for the inspections for corrosion, wear, fatigue
Airworthiness Directive 2015–0038, dated
March 4, 2015, for related information. This
repetitive replacements of the fixed cracking, and loose studs of each
MCAI may be found in the AD docket on the fairing upper and lower attachment forward stud assembly of the fixed
Internet at http://www.regulations.gov by studs. We are issuing this AD to prevent fairing door upper and lower forward
searching for and locating Docket No. FAA– in-flight detachment of an MLG fixed attachment of both LH and RH MLG;
2015–6539. fairing and consequent damage to the and replacement if necessary. The
(2) For service information identified in airplane.
this AD, contact Airbus, Airworthiness NPRM also proposed an optional
DATES: This AD becomes effective June terminating modification for the
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; 6, 2016. repetitive replacements of the fixed
telephone +33 5 61 93 36 96; fax +33 5 61 The Director of the Federal Register fairing upper and lower attachment
93 44 51; email account.airworth-eas@ approved the incorporation by reference studs. We are issuing this AD to prevent
airbus.com; Internet http://www.airbus.com. of certain publications listed in this AD in-flight detachment of an MLG fixed
You may view this service information at the as of June 6, 2016. fairing and consequent damage to the
FAA, ADDRESSES: You may examine the AD airplane.
Transport Airplane Directorate, 1601 Lind docket on the Internet at http:// The European Aviation Safety Agency
Avenue SW., Renton, WA. For information
on the availability of this material at the
www.regulations.gov by searching for (EASA), which is the Technical Agent
FAA, call 425–227–1221. and locating Docket No. FAA–2015– for the Member States of the European
2458; or in person at the Docket Union, has issued EASA Airworthiness
(n) Material Incorporated by Reference Management Facility, U.S. Department Directive 2015–0001R1, dated January
None. of Transportation, Docket Operations, 15, 2015 (referred to after this as the
Issued in Renton, Washington, on April 20, M–30, West Building Ground Floor, Mandatory Continuing Airworthiness
2016. Room W12–140, 1200 New Jersey Information, or ‘‘the MCAI’’), to correct
John P. Piccola, Jr., Avenue SE., Washington, DC. an unsafe condition for all Airbus
Acting Manager, Transport Airplane
For service information identified in Model A318, A319, A320, and A321
Directorate, Aircraft Certification Service. this final rule, contact Airbus, series airplanes. The MCAI states:
[FR Doc. 2016–10117 Filed 4–29–16; 8:45 am]
Airworthiness Office—EIAS, 1 Rond Several occurrences of in-flight loss of
Point Maurice Bellonte, 31707 Blagnac main landing gear (MLG) fixed and hinged
BILLING CODE 4910–13–P
Cedex, France; telephone +33 5 61 93 36 fairings were reported. The majority of
96; fax +33 5 61 93 44 51; email reported events occurred following
DEPARTMENT OF TRANSPORTATION account.airworth-eas@airbus.com; scheduled maintenance activities. One result
Internet http://www.airbus.com. You of the investigation was that a discrepancy
Federal Aviation Administration may view this referenced service between the drawing and the maintenance
information at the FAA, Transport manuals was discovered. The maintenance
Airplane Directorate, 1601 Lind Avenue documents were corrected to prevent mis-
14 CFR Part 39 rigging of the MLG fixed and hinged fairings,
SW., Renton, WA. For information on which could induce fatigue cracking.
[Docket No. FAA–2015–2458; Directorate the availability of this material at the
Identifier 2014–NM–122–AD; Amendment Airbus issued Service Bulletin (SB) A320–
39–18468; AD 2016–07–23]
FAA, call 425–227–1221. It is also 52–1083, providing instructions for a one-
available on the Internet at http:// time inspection of the MLG fixed fairing
mstockstill on DSK3G9T082PROD with RULES
RIN 2120–AA64 www.regulations.gov by searching for composite insert and the surrounding area,
and locating Docket No. FAA–2015– replacement of the adjustment studs at the
Airworthiness Directives; Airbus 2458. lower forward position and adjustment to the
Airplanes new clearance tolerances. That SB was
FOR FURTHER INFORMATION CONTACT: replaced by Airbus SB A320–52–1100 (mod
AGENCY: Federal Aviation Sanjay Ralhan, Aerospace Engineer, 27716) introducing a re-designed location
Administration (FAA), Department of International Branch, ANM–116, stud, rod end and location plate at the
Transportation (DOT). Transport Airplane Directorate, FAA, forward upper and lower leg fixed-fairing
VerDate Sep<11>2014 17:39 Apr 29, 2016 Jkt 238001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 E:\FR\FM\02MYR1.SGM 02MYR1](https://thefederalregister.org/doc/81_FR_26197/page/3.svg)
Document Created: 2016-04-30 13:35:37
Document Modified: 2016-04-30 13:35:37
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective June 6, 2016. | |
| 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. | |
| FR Citation | 81 FR 26113 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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