## 5362 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations

www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Kansas City, Missouri, on January 6, 2017. Melvin Johnson, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2017–00502 Filed 1–17–17; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–0831; Directorate Identifier 2014–NM–061–AD; Amendment**  **39–18778; AD 2017–01–11]**

**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 and A319 series airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, and Model A321 series airplanes. This AD was prompted by a report of a rupture of a main landing gear (MLG) sliding tube axle. This AD requires identification of the part number and serial number of the MLG sliding tubes; inspection of affected chromium plates and sliding tube axles for damage; and replacement of the sliding tube if necessary. We are issuing this AD to address the unsafe condition on these products.

**DATES** 

### : This AD is effective February 22,
2017.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 22, 2017.

**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 account.airworth-eas@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–
0831. 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– 0831; 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 supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A318 and A319 series airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, and Model A321 series airplanes. The SNPRM published in the Federal Register on June 28, 2016 (81 FR 41886) (‘‘the SNPRM’’). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on April 24, 2015 (80 FR 22939) (‘‘the NPRM’’). The NPRM proposed to require an inspection to identify the part number and serial number of the MLG sliding tubes installed on the airplane; an inspection of the axle on certain MLG sliding tubes for damage; and replacement of the sliding tube if necessary. The NPRM was prompted by a report of a rupture of a MLG sliding tube axle. The SNPRM proposed to remove certain service information that does not adequately address the identified unsafe condition and revise the compliance method. We are issuing this AD to detect and correct cracks in the axle and (partial) detachment of the axle and wheel from the sliding tube, which could result in failure of an MLG.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0058, dated March 11, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318 and A319 series airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, and Model A321 series airplanes. The MCAI states:

A main landing gear (MLG) sliding tube axle rupture occurred in service. Investigation of the affected part showed that this failure was due to an abnormal grinding operation during overhaul by a certain maintenance and repair organization located in Singapore. A population of MLG sliding tubes was subsequently identified whose axles may have been subject to this grinding operation, which may have resulted in areas of residual stress on the axles on the MLG sliding tubes. In addition, the MSN [manufacturer serial number] of the aeroplanes which are known to have had the affected parts installed have been identified.

This condition, if not detected and corrected, could lead to cracks in the axle and (partial) detachment of axle and wheel from the sliding tube, possibly resulting in failure of a MLG with consequent damage to the aeroplane and injury to occupants.

To address this potential unsafe condition, Messier-Bugatti-Dowty, the MLG gear manufacturer, issued Service Bulletin (SB) 200–32–313 and SB 201–32–62 [both dated February 25, 2013], providing inspection instructions and criteria for removal from service of the affected MLG sliding tubes.

For the reasons described above, this [EASA] AD requires a one-time Special Detailed Inspection (SDI) of the axle on the affected MLG sliding tubes and, depending on findings, replacement of the MLG sliding tube.



### The SDI includes a detailed visual inspection of the chromium plate for damage, and a Barkhausen noise inspection of the sliding tube axles for damage.

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–
0831.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data 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 SNPRM for correcting the unsafe condition; and


## 5363 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations

• Do not add any additional burden upon the public than was already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

Airbus has issued Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014. This service information describes procedures for inspecting MLG axles and brake flanges by doing a detailed visual inspection of the chromium plates for damage, a Barkhausen noise inspection of the sliding tube axles for damage, and replacement of affected parts 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 also estimate that it would take about 18 work-hours 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 $4,590, or $1,530 per product.

In addition, we estimate that any necessary on-condition actions will take about 3 work-hours, for a cost of $255 per product. We have received no definitive data that would enable us toprovide part cost estimates for the oncondition actions specified in this AD. We have no way of determining the number of aircraft that might need these actions. 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** 

■ 

### 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):

2017–01–11 Airbus: Amendment 39–18778; Docket No. FAA–2015–0831; Directorate Identifier 2014–NM–061–AD. (a) Effective Date This AD is effective February 22, 2017.

(b) Affected ADs

None.
(c) Applicability

This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers.

(1) Airbus Model A318–111, –112, –121, and –122 airplanes.

(2) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes.

(3) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes.

(4) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes.
(d) Subject

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

(e) Reason

This AD was prompted by a report of a rupture of a main landing gear (MLG) sliding tube axle. We are issuing this AD to detect and correct cracks in the axle and (partial) detachment of the axle and wheel from the sliding tube, which could result in failure of an MLG.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) MLG Sliding Tube Part Number and Serial Number Identification

Within 3 months after the effective date of this AD: Do an inspection to identify the part number and serial number of the MLG sliding tubes installed on the airplane. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number and serial number of the MLG sliding tubes can be conclusively determined from that review.
(h) Identification of Airplanes Not Affected by the Requirements of Paragraph (i) of this AD

An airplane with a manufacturer serial number (MSN) not listed in figure 1 to paragraph (h) of this AD is not affected by the requirements of paragraph (i) of this AD, provided it can be determined that no MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD has been installed on that airplane since first flight of the airplane.



### F IGURE 

### 1 TO 

### PARAGRAPH 

### ( H 

### ) OF 

### THIS 

### AD

Affected Airplanes Listed by MSN

0179 0214 0296 0412 0558 0604 0607 0668 0704 0720 0726 0731 0754 0771 0799 0828 0841 0855 0909 0914 0925 0939 0986 1028 1030 1041 1070 1083 1093 1098


## 5364 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations

F IGURE 

### 1 TO 

### PARAGRAPH 

### ( H 

### ) OF 

### THIS 

### AD—Continued

1108 1148 1294 1356 2713 2831



### TABLE 

### 1 TO 

### PARAGRAPHS 

### (h), (i), (k)(1), (k)(2), (l)(1), AND 

### (l)(2) OF
THIS 

### AD—A FFECTED 

### MLG S LIDING 

### T UBES

Part No. Serial No.

201160302 ............................ 78B 201160302 ............................ 1016B11 201160302 ............................ 1144B 201371302 ............................ B4493 201371302 ............................ B4513 201371302 ............................ SS4359 201371302 ............................ B4530 201371302 ............................ B4517 201371302 ............................ B4568 201371302 ............................ B4498 201371302 ............................ 4490B 201371302 ............................ B202–4598 201371302 ............................ B165–4623 201371302 ............................ B244–4766 201371302 ............................ B267–4794 201371302 ............................ B272–4813 201160302 ............................ 1108B 201371304 ............................ B041–4871 201371304 ............................ B045–4869 201371304 ............................ B001–4781 201371304 ............................ B051–4892 201371304 ............................ B110–1952 201371304 ............................ B054–4891 201371304 ............................ B063–4921 201371304 ............................ B071–4911 201371304 ............................ B071–4917 201371304 ............................ B080–1933 201371304 ............................ B117–5010 201371304 ............................ B120–4989 201371304 ............................ B132–2023 201371304 ............................ B114–1956 201371304 ............................ B208–2009 201371304 ............................ B133–1947 201371304 ............................ B154–5037 201371304 ............................ B89 4952 201371304 ............................ B129–1964 201371304 ............................ B227–2010 201371304 ............................ B170–5031 201371304 ............................ B182–5047 201371304 ............................ B239–2053 201371304 ............................ B1401–2856 201371304 ............................ B1813–3142 201371304 ............................ B116–5004 201522353 ............................ B011–149 201522350 ............................ B014–25 201522350 ............................ B019–56 201522350 ............................ B019–57 201522350 ............................ B021–69 201522350 ............................ B022–60 201522353 ............................ B03–111 201522353 ............................ B03–110 201522353 ............................ B112–317 201522353 ............................ B174–351 201522353 ............................ B179–392 201383350 ............................ 4377B 201383350 ............................ 4393B 201383350 ............................ B1831 201383350 ............................ B1832 201383350 ............................ SS4355B 201383350 ............................ SS4400B

(i) Inspections

For each MLG sliding tube identified as required by paragraph (g) of this AD, having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: Within 3 months after the effective date of this AD, inspect affected MLG axles and brake flanges by doing a detailed visual inspection of the chromium plates for damage, and a Barkhausen noise inspection of the sliding tube axles for damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014. For Model A318 series airplanes, use the procedures specified for Model A319 series airplanes in Airbus Service Bulletin A320– 32–1416, including Appendix 01, dated March 10, 2014.
(j) Corrective Action

If, during any inspection required by paragraph (i) of this AD, any damage is detected: Before further flight, replace the MLG sliding tube with a serviceable tube, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1416, including Appendix 01, dated March 10, 2014. For Model A318 series airplanes, use the procedures specified for Model A319 series airplanes in Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014.
(k) Definition of Serviceable Sliding Tube

For the purpose of this AD, a serviceable sliding tube is defined as a sliding tube that meets the criterion in either paragraph (k)(1) or (k)(2) of this AD.

(1) A sliding tube having a part number and serial number not listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD.

(2) A sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD that has passed the inspections required by paragraph (i) of this AD.
(l) Parts Installation Prohibitions

(1) For airplanes that have an MLG sliding tube installed that has a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: After an airplane is returned to service following accomplishment of the actions required by paragraphs (g), (h), and (i) of this AD, no person may install on any airplane an MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD unless that sliding tube has passed the inspection required by paragraph (i) of this AD.

(2) For airplanes that, as of the effective date of this AD, do not have an MLG sliding tube installed that has a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: No person may install on any airplane an MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD unless that sliding tube has passed the inspection required by paragraph (i) of this AD.
(m) 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. The AMOC approval letter must specifically reference this AD.

(2) Required for Compliance (RC): 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.

(3) 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 European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(n) Special Flight Permits

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 to a location where the airplane can be modified (if the operator elects to do so), provided the MLG remains extended throughout the flight.
(o) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA


## 5365 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations

Airworthiness Directive 2014–0058, dated March 11, 2014, 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–
2015–0831. (p) 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 A320–32–1416, including Appendix 01, dated March 10,
2014.

(ii) Reserved. (3) 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 account.airworth-eas@ airbus.com; Internet http://www.airbus.com.

(4) 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.

(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 January 4, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2017–00408 Filed 1–17–17; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–9058; Directorate Identifier 2016–NM–024–AD; Amendment**  **39–18771; AD 2017–01–04]**

**RIN 2120–AA64**



### Airworthiness Directives; Fokker **Services B.V. Airplanes**

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. This AD was prompted by an analysis which determined that, for certain areas of the fuselage, the current threshold of an Airworthiness Limitations Section inspection is insufficient to detect early crack development. This AD requires one time high and low frequency eddy current inspections of the affected fuselage skin for cracks, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.

**DATES** 

### : This AD is effective February 22,
2017.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 22, 2017.

**ADDRESSES** 

### : For service information identified in this final rule, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone: +31 (0)88–6280–350; fax: +31 (0)88– 6280–111; email: technicalservices@ fokker.com; Internet http:// www.myfokkerfleet.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–2016–
9058. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9058; 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** 

### : Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; 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 certain Fokker Services B.V. Model F28 Mark 0100 airplanes. The NPRM published in the Federal Register on September 8, 2016 (81 FR 62029) (‘‘the NPRM’’). The NPRM was prompted by an analysis which determined that, for certain areas of the fuselage, the current threshold of an Airworthiness Limitations Section inspection is insufficient to detect early crack development. The NPRM proposed to require one time high and low frequency eddy current inspections of the affected fuselage skin for cracks, and repair if necessary. We are issuing this AD to detect and correct cracks in the fuselage skin; such cracking could result in reduced structural integrity of the fuselage.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive Airworthiness Directive 2016– 0029R1, dated November 17, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. The MCAI states:

A complementary fatigue and damage tolerance analysis was accomplished by the design approval holder on the traffic collision avoidance system (TCAS) antenna installation on the top of the fuselage between station (STA) 6805 and STA7305. Based on the results, it was determined that for the affected area, the current 58 000 flight cycles (FC) threshold of Airworthiness Limitations Section (ALS) inspection task 533001–00–20 and 533028–00–20 (special detailed inspection of longitudinal lap joints) is insufficient to timely detect possible crack development.

This condition, if not detected and corrected, could affect the structural integrity of the fuselage in this area.

To address this potential unsafe condition, Fokker Services published Service Bulletin (SB) SBF100–53–130 to provide inspection instructions.

Consequently, EASA issued AD 2016–0029 to require a one-time inspection of the fuselage skin around the largest TCAS antenna external doubler and of the longitudinal lap joint at stringer (STR) 37 between fuselage STA6805 and STA7305.

Since that [EASA] AD was issued, it was discovered that another ALS inspection task, 533028–00–20, is also related to this subject. This [EASA] AD is revised to clarify that the inspection threshold of both ALS inspection tasks has been re-assessed. It is expected that a repetitive inspection task will be included in the ALS, which will cover only the area close to the TCAS antenna installation. For the remainder of the affected lap joint, no change is anticipated and this will therefore continue to be inspected in accordance with the existing ALS tasks.

This [EASA] AD is still considered to be an interim action and further [EASA] AD