### 68429 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations

manages the Agency’s chartering activities; and analyzes policy and strategic risks to the System.

(6) Office of Management Services. The Office of Management Services provides financial management services. It administers the Agency’s human resources management program, contracts, procurement, mail services, and payroll.

(7) Office of Secondary Market Oversight. The Office of Secondary Market Oversight regulates and examines the Federal Agricultural Mortgage Corporation for safety and soundness and compliance with law and regulations.

(8) Secretary to the Board. The Secretary to the Board serves as the parliamentarian for the Board and keeps permanent and complete records and minutes of the acts and proceedings of the Board.

(9) Office of the Chief Operating Officer. The Chief Operating Officer has broad responsibility for planning, directing, and controlling the operations of the Offices of Management Services, Information Technology, Examination, Regulatory Policy, and General Counsel in accordance with the operating philosophy and policies of the FCA Board.

(10) Designated Agency Ethics Official. The Designated Agency Ethics Official is designated by the FCA Chairman to administer the provisions of title I of the Ethics in Government Act of 1978, as amended, to coordinate and manage FCA’s ethics program, and to provide liaison to the Office of Government Ethics with regard to all aspects of FCA’s ethics program.

(11) Office of Information Technology. The Office of Information Technology manages information resources management program and delivers the Agency’s information technology, data analysis infrastructure, and the security supporting Agency technology

resources.

(12) Equal Employment Opportunity and Inclusion. The Office of Equal Employment Opportunity and Inclusion manages and directs the Agency-wide Diversity, Inclusion, and Equal Employment Opportunity Program for FCA and FCSIC. The office serves as the chief liaison with the Equal Employment Opportunity Commission and the Office of Personnel Management on all Equal Employment Opportunity, diversity, and inclusion issues. The office provides counsel and leadership to Agency management to carry out its continuing policy and program of nondiscrimination, affirmative action, and diversity. (b) Additional Information. You may obtain more information on the FCA’s organization by visiting our Web site at http://www.fca.gov. You may also contact the Office of Congressional and Public Affairs:

(1) In writing at FCA, 1501 Farm Credit Drive, McLean, Virginia 22102– 5090;

(2) By email at info-line@fca.gov; or (3) By telephone at (703) 883–4056.

**PART 606—ENFORCEMENT OF NONDISCRIMINATION ON THE BASIS**  **OF HANDICAP IN PROGRAMS OR ACTIVITIES CONDUCTED BY THE**  **FARM CREDIT ADMINISTRATION**

■ 4. The authority citation for part 606 continues to read as follows:

Authority: 29 U.S.C. 794.

**§ 606.670 [Amended]**

■ 5. Amend § 606.670 by removing the words ‘‘Director, Equal Employment Opportunity’’ and adding in their place, the words ‘‘Equal Employment Opportunity and Inclusion Director’’ in paragraph (i).

Dated: October 30, 2015. Dale L. Aultman, Secretary, Farm Credit Administration Board.
[FR Doc. 2015–28244 Filed 11–4–15; 8:45 am]

**BILLING CODE 6705–01–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–4211; Directorate Identifier 2015–NM–150–AD; Amendment**  **39–18311; AD 2015–22–06]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

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

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of spoiler and elevator computer (SEC) latent failures; an undetected loss of a SEC in flight will result in loss in redundancy for elevator control. This AD requires revising the After Start Normal Procedures section of the airplane flight manual (AFM) to provide procedures that will address this loss of redundancy. We are issuing this AD to ensure that the flightcrew has procedures to address loss of redundancy of SEC 1 and SEC 2. A SEC failure, in conjunction with a loss of trimmable horizontal stabilizer (THS) electrical control due to jamming or rupture, could result in failure of an elevator and aileron computer, and consequent loss of elevator control and reduced control of the airplane.

**DATES :**  This AD becomes effective November 20, 2015.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 20, 2015.

We must receive comments on this AD by December 21, 2015.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this 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.airwortheas@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–2015–4211. 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– 4211; or in person at the Docket Operations office 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


### 68430 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations

other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**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

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0191, dated September 22, 2015 (correction September 25, 2015) (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318, A319, A320, and A321 series airplanes. The MCAI states:

With the introduction of new Spoiler and Elevator Computer (SEC) hardware C Part Number (P/N) B372CAM0100 with software standards 122, 124 and 125 (identified by P/ N B372CAM0101, P/N B372CAM0102 and P/ N B372CAM0103, respectively), some airlines have reported receiving maintenance
messages, e.g. ‘‘SEC OR WIRING FROM L or R ELEV POS MON XDCR’’ and/or ‘‘SEC OR WIRING FROM G or Y ELEV POS XDCR’’, which are associated with servo control or elevator transducer monitoring. Such messages are triggered by a short data inconsistency due to power transients, when the engines are started.

This condition, if not corrected, could lead to an undetected loss of redundancy during flight if an affected SEC cannot control the related elevator servo control(s), possibly resulting in reduced control of the aeroplane.

It was determined that, to recover full redundancy, a reset of SEC 1 and SEC 2 must be done after engines start and Airbus have developed an Airplane Flight Manual (AFM) Temporary Revision (TR), published as TR 572 Issue 1.1, to provide the necessary flight crew procedure.

Required actions include revising the After Start Normal Procedures section of the AFM to provide procedures that will address this loss of redundancy. You may examine the MCAI on the Internet
at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–4211.

Related Service Information Under 1 CFR Part 51

Airbus has issued A318/A319/A320/ A321 Temporary Revision TR572, Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/A320/A321 Airplane Flight Manual. The service information describes the reset of SEC 1 and SEC 2 that must be done after engines start. 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 of this AD. FAA’s Determination and Requirements of This AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs.

FAA’s Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because a SEC failure in conjunction with a loss of THS electrical control due to jamming or rupture, could result in failure of an elevator and aileron computer, and consequent loss of elevator control and reduced control of the airplane. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA–2015–4211; Directorate Identifier 2015–NM–150– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD based on those
comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance

We estimate that this AD affects 959 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 $81,515, or $85 per product. Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings

We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify 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.


### 68431 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations

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):

2015–22–06 Airbus: Amendment 39–18311. Docket No. FAA–2015–4211; Directorate Identifier 2015–NM–150–AD.

(a) Effective Date

This AD becomes effective November 20,

2015.
(b) Affected ADs

None.
(c) Applicability

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

(1) Airbus Model A318–111, –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 27, Flight Controls.

(e) Reason

This AD was prompted by reports of spoiler and elevator computer (SEC) latent failures; an undetected loss of a SEC in flight will result in loss in redundancy for elevator control. This AD requires revising the After Start Normal Procedures section of the airplane fight manual (AFM) to provide procedures that will address this loss of redundancy. We are issuing this AD to ensure that the flightcrew has procedures to address loss of redundancy of SEC 1 and SEC 2. A SEC failure, in conjunction with a loss of trimmable horizontal stabilizer (THS) electrical control due to jamming or rupture, could result in failure of an elevator and aileron computer, and consequent loss of elevator control and reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done.
(g) Airplane Flight Manual Revision

For airplanes equipped with SEC hardware C part number (P/N) B372CAM0100 with software standard 122 (P/N B372CAM0101), 124 (P/N B372CAM0102), or 125 (P/N B372CAM0103), on SEC position 1 or 2, or both: Within 30 days after the effective date of this AD, revise the After Start Normal Procedures section of the AFM to include the statement specified in figure 1 to paragraph (g) of this AD. This may be done by inserting a copy of this AD, or Airbus A318/A319/ A320/A321 Temporary Revision TR572, Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/A320/A321 Airplane Flight Manual, into the applicable AFM.



### F IGURE 

### 1 TO 

### PARAGRAPH 

### (g) OF 

### THIS



### AD—AFM TEMPORARY 

### R EVISION

AFTER START NORMAL PROCEDURE After both engines start: Turn OFF then ON SEC 1 and SEC 2 one

after another.

Note 1 to paragraph (g) of this AD: When a statement identical to that in figure 1 to paragraph (g) of this AD has been included in the After Start Normal Procedures section of the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD or Airbus A318/A319/A320/A321 Temporary Revision TR572, Issue 1.0, dated August 13, 2015, may be removed from the AFM.

Note 2 to paragraph (g) of this AD: Airbus Operations Engineering Bulletin OEB–50 provides additional information on the subject addressed by this AD.

(h) Optional Modification

Modification of an airplane by installation of SEC hardware C with software standard 126 (P/N B372CAM0104) (Airbus Modification 161208) allows removal of the AFM revision required by paragraph (g) of this AD for that airplane.
(i) Parts Installation Limitation

For all airplanes: As of the effective date of this AD, do not install SEC hardware C P/ N B372CAM0100 with software standard 122 (P/N B372CAM0101), 124 (P/N B372CAM0102), or 125 (P/N B372CAM0103), on SEC position 1 or 2, or both, on any airplane, unless the AFM of the airplane is revised concurrently with that installation, as required by paragraph (g) of this AD.
(j) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: 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) 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.
(k) 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.

(l) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0191, dated September 22, 2015 (corrected September 25, 2015), for related information. You may examine the MCAI on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–4211.
(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 this AD specifies otherwise.

(i) Airbus A318/A319/A320/A321 Temporary Revision TR572, Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/ A320/A321 Airplane Flight Manual.

(ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@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://


### 68432 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations

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

Issued in Renton, Washington, on October 22, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–27688 Filed 11–4–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–1425; Directorate Identifier 2014–NM–185–AD; Amendment**  **39–18312; AD 2015–22–07]**

**RIN 2120–AA64**

**Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin**  **Aeronautics Company Airplanes**

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the circumferential fuselage splice at fuselage-station (FS) 695 is subject to widespread fatigue damage (WFD). This AD requires an inspection for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of certain stringers, inspection for cracking and modification of certain fastener holes common to the stringer and splice member at the forward and aft ends of the splice, and related investigative and corrective actions if necessary. We are issuing this AD to prevent loss of residual strength of the circumferential fuselage splice at FS 695, which could lead to rapid decompression of the cabin and potential loss of the airplane.

**DATES :**  This AD is effective December 10, 2015.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 10, 2015.

**ADDRESSES :**  For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P–58, 86 S. Cobb Drive, Marietta, GA 30063; phone: 770–494–5444; fax: 770– 494–5445; email: ams.portal@lmco.com; Internet http:// www.lockheedmartin.com/ams/tools/ TechPubs.html. 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–2015–1425. 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– 1425; 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 :**  Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5554; fax: 404– 474–5605; email: carl.w.gray@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 Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. The NPRM published in the Federal Register on May 28, 2015 (80 FR 30391). The NPRM was prompted by an evaluation by the DAH indicating that a certain circumferential fuselage splice is subject to WFD. The NPRM proposed to require an inspection for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of certain stringers, inspection for cracking and modification of certain fastener holes common to the stringer and splice member at the forward and aft ends of the splice, and related investigative and corrective actions if necessary. We are issuing this AD to prevent loss of residual strength of a certain circumferential fuselage splice, which could lead to rapid decompression of the cabin and potential loss of the airplane.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 30391, May 28, 2015) 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 NPRM (80 FR 30391, May 28, 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 30391, May 28, 2015).

Related Service Information Under 1 CFR Part 51

We reviewed Lockheed Martin Electra Service Bulletin 88/SB–722, dated April 30, 2014. This service bulletin describes procedures for doing the following actions:

• A general visual inspection (GVI) for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of stringers 1–7 and 66–72, and corrective actions if necessary.

• At stringers 1–7 and 66–72, removing the four rivets common to the stringer and splice member at the forward and aft ends of the splice and doing a bolt hole eddy current (BHEC) inspection or an equivalent inspection procedure for cracking in each of the fastener holes, and corrective actions if
necessary.

• Corrective actions for cracked holes include reaming to the maximum permissible hole diameter of the next larger size rivet. If a crack indication remains after reaming, this service information specifies repairing the cracked stringer.

• If a severed stringer is found during the GVI, doing related investigative actions of an eddy current surface scan inspection for cracking of the fuselage skin at the skin-to-stringer attachments immediately forward and aft of the stringer break and confirming skin cracks with a dye penetrant inspection. Corrective actions include repairing the severed stringer or skin cracks.