### 1494 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations

2. Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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.

We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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** 

■ 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
2016–01–06 Agusta S.p.A.: Amendment 39– 18365; Docket No. FAA–2015–8695; Directorate Identifier 2015–SW–042–AD.
(a) Applicability

This AD applies to Model AB139 and AW139 helicopters, certificated in any category, with a Full Icing Protection System tail rotor slip ring (slip ring) part number (P/ N) 4G6420V00151, P/N 4G6420V00152, or P/ N 4G6420V00153 installed, except a slip ring with a letter ‘‘T’’ after the serial number or marked with ‘‘MOD 1.’’
(b) Unsafe Condition

This AD defines the unsafe condition as a loose or missing screw connecting the mounting flange and the slip ring body. This condition could result in separation of the mounting flange from the slip ring body and subsequent loss of control of the helicopter.

(c) Effective Date

This AD becomes effective January 28,
2016. (d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(e) Required Actions

Within 25 hours time-in-service: (1) Remove each slip ring from the helicopter. Remove each lockwire, fastener, and washer by following the Compliance Instructions, paragraphs 3 through 5, of Moog Service Bulletin SB 14–02, Revision D, undated, included as Annex A to Agusta Westland Bollettino Tecnico (BT) No. 139– 404, dated December 22, 2014, except you are not required to discard parts.

(2) Inspect the wall of the mounting plate hole for a chatter mark, witness mark, or scoring. If there is a chatter mark, witness mark, or scoring, replace the slip ring with a slip ring that is not listed in paragraph (a) of this AD.

(3) Determine the depth of the mounting plate hole. If the depth exceeds the grip length of the screw, replace the slip ring with a slip ring that is not listed in paragraph (a) of this AD.

(4) Re-identify the slip ring by marking a letter ‘‘T’’ after the serial number with permanent black pen and applying acrylic lacquer (CO81 or equivalent).

(5) Do not install an affected slip ring on any helicopter unless the slip ring has passed the inspections in accordance with this AD.
(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Martin R. Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.
(g) Additional Information

The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2015–0155, dated July 28, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2015–
8695. (h) Subject

Joint Aircraft Service Component (JASC) Code: 3060 Propeller/Rotor Anti-ice/De-Ice System. (i) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference 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 the AD specifies otherwise.

(i) AgustaWestland Bollettino Technico No. 139–404, dated December 22, 2014, including Annex A, Moog Service Bulletin SB 14–02, Revision D, undated.

(ii) Reserved. (3) For service information identified in this AD, contact Moog Inc., Components Group, Blacksburg Operations, 1213 North Main St., Blacksburg, Virginia 24606–3127, telephone 540/552–3011, or at
www.moog.com.

(4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110.

(5) 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: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Fort Worth, Texas, on December 28, 2015. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2016–00013 Filed 1–12–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–1990; Directorate Identifier 2015–NM–027–AD; Amendment**  **39–18364; AD 2016–01–05]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737–400 series airplanes, as modified by a certain supplemental type certificate. This AD was prompted by the discovery of a design drawing error regarding placards that identified incorrect squibs and pressure switches for certain fire extinguisher bottles. This AD requires a detailed inspection of certain cargo placards to determine if they are the correct placards and in the correct location, a detailed inspection of the harnesses to verify that they are marked and installed correctly, and corrective action if necessary. We are issuing this AD to detect and correct incorrectly installed harnesses for the cargo fire suppression system bottles, which could result in an incorrect activation sequence of the bottles, the inability to suppress a cargo fire quickly, and a possible uncontrollable fire.

**DATES :**  This AD is effective February 17,
2016.


### 1495 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 17, 2016.

**ADDRESSES :**  For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.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 http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–
1990. 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– 1990; 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 address for the Docket Office (phone: 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 :**  Paul DeVore, Aerospace Engineer, Systems and Propulsion Branch, ACE–116W, FAA, Wichita ACO, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, KS 67209; phone: 316–946– 4142; fax: 316–946–4107; email: paul.devore@faa.gov.

**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 certain The Boeing Company Model 737–400 series airplanes, as modified by a certain supplemental type certificate. The NPRM published in the Federal Register on July 2, 2015 (80 FR 38033). The NPRM was prompted by the discovery of a design drawing error regarding placards that identified incorrect squibs and pressure switches for certain fire extinguisher bottles. The NPRM proposed to require a detailed inspection of certain cargo placards to determine if they are the correct placards and in the correct location, a detailed inspection of the harnesses to verify that they are marked and installed correctly, and corrective action if necessary. We are issuing this AD to detect and correct incorrectly installed harnesses for the cargo fire suppression system bottles, which could result in an incorrect activation sequence of the bottles, the inability to suppress a cargo fire quickly, and a possible uncontrollable fire.

Comments

We gave the public the opportunity to participate in developing this AD. We have considered the comments received. The European Aviation Safety Agency stated that it is following the progress of this activity of the NPRM (80 FR 38033, July 2, 2015). Boeing stated that the NPRM does not address any Boeing designs; therefore, Boeing can neither review the data, nor comment on the content of the NPRM, and that no file attachment accompanies its comment. Conclusion
We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (80 FR 38033, July 2, 2015) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 38033, July 2, 2015).

Related Service Information Under 1 CFR Part 51

We reviewed Advanced Aircraft Extinguishers Service Bulletin TFA10– 26–0020, Revision IR, dated January 12, 2015. The service information describes procedures for a detailed inspection of Advanced Aircraft Extinguishers cargo fire protection system placards to determine if they are the correct placards and in the correct location, and applicable corrective actions; and a detailed inspection of the harnesses to verify that they are correctly marked and installed, and doing steps C.(5) through C.(11) of Advanced Aircraft Extinguishers Service Bulletin TFA10– 26–0020, Revision IR, dated January 12, 2015, if necessary. 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 3 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### C OSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Detailed inspection .......................................... 2 work-hours × $85 per hour = $170 ............. N/A $170 $510

We estimate the following costs to do any necessary corrective actions that will be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these corrective actions:



### O N 

### -C ONDITION 

### C OSTS

Action Labor cost Parts cost Cost per product

Corrective actions ......................................................... 2 work-hours × $85 per hour = $170 ........................... $900 $1,070


### 1496 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations

According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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

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 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** 

■ 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
2016–01–05 The Boeing Company: Amendment 39–18364; Docket No. FAA–2015–1990; Directorate Identifier 2015–NM–027–AD.
(a) Effective Date

This AD is effective February 17, 2016.

(b) Affected ADs

None. (c) Applicability

This AD applies to The Boeing Company Model 737–400 series airplanes, certificated in any category, having serial numbers 23865, 24231, 24706, 24474, 25417, 27003, 27149, 25375, 26281, 28661, and 28881, as modified by Supplemental Type Certificate ST01114WI ( http://rgl.faa.gov/Regulatory

_ and

_ Guidance

_Library/rgstc.nsf/0/ f9490633c04cbc8286257301006ed621/$FILE/ ST01114WI.pdf ).
(d) Subject

Air Transport Association (ATA) of America Code 26, Fire Protection.

(e) Unsafe Condition

This AD was prompted by the discovery of a design drawing error regarding placards that identified incorrect squibs and pressure switches for certain fire extinguisher bottles. We are issuing this AD to detect and correct incorrectly installed harnesses for the cargo fire suppression system bottles, which could result in an incorrect activation sequence of the bottles, the inability to suppress a cargo fire quickly, and a possible uncontrollable fire.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Placard Inspection

Within 6 months after effective date of this AD, do a detailed inspection of Advanced Aircraft Extinguishers cargo fire protection system (FPS) placards to determine if they are the correct placards and in the correct location, and do all applicable corrective actions, in accordance with the ‘‘SERVICE BULLETIN INSTRUCTIONS’’ of Advanced Aircraft Extinguishers Service Bulletin TFA10–26–0020, Revision IR, dated January 12, 2015. Do all applicable corrective actions before further flight.
(h) Harness Inspection

Within 6 months after the effective date of this AD, do a detailed inspection of the harnesses to verify that they are correctly marked and installed, in accordance with the ‘‘SERVICE BULLETIN INSTRUCTIONS’’ of Advanced Aircraft Extinguishers Service Bulletin TFA10–26–0020, Revision IR, dated January 12, 2015. If any harness is not marked or installed correctly, before further flight, do steps C.(5) through C.(11) specified in and in accordance with the ‘‘SERVICE BULLETIN INSTRUCTIONS’’ of Advanced Aircraft Extinguishers Service Bulletin TFA10–26–0020, Revision IR, dated January 12, 2015, except as required by paragraph (i) of this AD.
(i) Exception to the Service Information Specification

Where Advanced Aircraft Extinguishers Service Bulletin TFA10–26–0020, Revision IR, dated January 12, 2015, specifies contacting the manufacturer for appropriate action: Before further flight, repair in accordance with a method approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA.
(j) Special Flight Permit

Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane, provided the airplane does not carry cargo in the lower cargo bay.
(k) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Wichita ACO, 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 manager of the ACO, send it to the attention of the person identified in paragraph (l) of this AD.

(2) 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.

(3) Except as required by paragraph (i) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(3)(i) and (k)(3)(ii) of this AD apply.

(i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures.

(ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.

(l) Related Information

For more information about this AD, contact Paul C. DeVore, Aerospace Engineer, Systems and Propulsion Branch, ACE–116W, FAA, Wichita ACO, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita,


### 1497 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations

KS 67209; phone: 316–946–4142; fax: 316– 946–4107; email: paul.devore@faa.gov.
(m) 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 the AD specifies otherwise.

(i) Advanced Aircraft Extinguishers Service Bulletin TFA10–26–0020, Revision IR, dated January 12, 2015.

(ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com.

(4) You may view this service information at 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.

(5) 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: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Renton, Washington, on December 28, 2015. Philip Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016–00004 Filed 1–12–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–0937; Directorate Identifier 2014–NM–024–AD; Amendment**  **39–18348; AD 2015–25–10]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding Airworthiness Directive (AD) 2011–24– 05 for certain Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes, and Model A340–200 and –300 series airplanes. AD 2011–24– 05 required repetitive inspections for cracking of the hole(s) of the horizontal flange of the keel beam, and repair if necessary. This new AD requires changing the inspection compliance times, and, for certain airplanes, adding a one-time ultrasonic inspection for cracking at a certain fastener hole. This new AD also provides optional terminating action for the repetitive inspections. This AD was prompted by a determination that the rototest inspection and applicable corrective actions of a certain fastener hole were inadvertently omitted from the requirements in AD 2011–24–05. We are issuing this AD to detect and correct cracking of the fastener holes, which could result in rupture of the keel beam, and consequent reduced structural integrity of the airplane.

**DATES :**  This AD becomes effective February 17, 2016.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 17, 2016.

The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 3, 2012 (76 FR 73496, November 29, 2011).

The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of September 13, 2007 (72 FR 44731, August 9, 2007).

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0937; or in person at the 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.

For service information identified in this final rule, 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 airworthiness.A330-A340@airbus.com; 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–
0937.

**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 425–227–1138; fax 425–227–1149.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011). AD 2011–24–05 applied to certain Airbus Model A330– 201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–200 and –300 series airplanes. The NPRM published in the Federal Register on May 4, 2015 (80 FR 25249).

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0010R1, dated May 5, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–200 and –300 series airplanes. The MCAI states:

During A330 and A340 aeroplanes fatiguetests, cracks were detected on the RH [righthand] and LH [left-hand] sides between the crossing area of the keel beam fitting and the front spar of the Centre Wing Box (CWB).

This condition, if not detected and corrected, could lead to keel beam rupture which would affect the structural integrity of the area.

Prompted by this potential unsafe condition, EASA issued AD 2006–0315 [ http://ad.easa.europa.eu/blob/easa

_ ad

_ 2006

_ 0315.pdf/AD

_ 2006-0315 ] (later revised to R1) to require repetitive special detailed inspections (SDI) [rotating probe inspection for cracking] on the horizontal flange of the keel beam in the area of first fastener hole aft of Frame (FR) 40 in order to maintain the structural integrity of the aeroplane.

After that [EASA] AD was issued, EASA issued AD 2010–0024 [which corresponds to FAA AD 2011–24–05, Amendment 39–16869 (76 FR 73496, November 29, 2011)], retaining the inspection requirements of EASA AD 2006–0315R1 [ http://ad.easa.europa.eu/blob/

easa

_ ad

_2006

_ 0315R1.pdf/AD

_ 2006- 0315R1 ], which was superseded, extending the applicability to aeroplanes with Airbus Mod 49202 embodied, and reducing the inspection thresholds and intervals.

Since that [EASA] AD [2010–0024] was issued, a new fatigue and damage tolerance evaluation has been conducted by Airbus, which concluded that due to the aeroplane utilization, the current inspection threshold and intervals have to be modified.

In addition, it was determined that the rototest inspection of fastener hole Nr 6, necessary to ensure that no crack was left unrepaired at the time of fastener hole cold working, was inadvertently not included in