1870 Federal Register / Vol. 81, No. 9 / Thursday, January 14, 2016 / Rules and Regulations 

priority project in each state, up to 7 

points for the second highest priority 

project in each state and up to 5 points 

for the third highest priority project that 

address unforeseen exigencies or 

emergencies, such as the loss of a 

community facility due to an accident 

or natural disaster, or other areas of 

need in their particular state. The State 

Director will place written 

documentation in the project file each 

time the State Director assigns these 

points—Up to 10 points. 

(i) Administrator discretionary points. 

The Administrator may award up to 20 

discretionary points for projects to 

address geographic distribution of 

funds, emergency conditions caused by 

economic problems, natural disasters 

and other initiatives identified by the 

Secretary—Up to 20 points. 

§ 3570.274 Fund disbursement. 

The Agency will make payments 

under this agreement in accordance 

with 2 CFR 200.305. All requests for 

advances or reimbursements must be in 

compliance with 2 CFR 200.306 and 

include any required matching fund 

usage. 

§ 3570.275 Grant cancellation or major 

changes. 

Any change in the scope of the 

Project, budget adjustments of more 

than 10 percent of the total budget, and 

any other significant change in the 

Project must be in compliance with 2 

CFR 200.308 and 200.339. The changes 

must be requested in writing and 

approved by the Agency in writing. Any 

change not approved may be cause for 

termination of the grant. 

§ 3570.276 Reporting. 

(a) The Grantee must provide periodic 

reports as required by the Agency. A 

financial status report, SF 425 ‘‘Federal 

Financial Report,’’, and a project 

performance report will be required as 

provided in the grant agreement. The 

financial status report must show how 

grant funds and matching funds have 

been used to date. A final report may 

serve as the last report. Grantees shall 

constantly monitor performance to 

ensure that time schedules are being 

met and projected goals by time periods 

are being accomplished. The Project 

performance reports shall include, but 

are not limited to, the following: 

(1) A description of the activities that 

the funds reflected in the financial 

status report were used for; 

(2) A comparison of actual 

accomplishments to the objectives for 

that period; 

(3) Reasons why established 

objectives were not met, if applicable; 

(4) Problems, delays, or adverse 

conditions which will affect attainment 

of overall program objectives, prevent 

meeting time schedules or objectives, or 

preclude the attainment of particular 

objectives during established time 

periods. This disclosure shall be 

accomplished by a Statement of the 

action taken or planned to resolve the 

situation; 

(5) Objectives and timetables 

established for the next reporting 

period; 

(6) A summary of the race, sex, and 

national origin of the Ultimate 

Recipients; 

(7) The final report will also address 

the following: 

(i) What have been the most 

challenging or unexpected aspects of 

this grant? 

(ii) What advice would you give to 

other organizations planning a similar 

grant? What are the strengths and 

limitations of this grant? If you had the 

opportunity, what would you have done 

differently? 

(iii) Are there any post-grant plans for 

this Project? If yes, how will they be 

financed? 

(b) [Reserved] 

§ 3570.277 Audit or financial statement. 

The Grantee will provide an Audit 

report or financial Statement in 

accordance with 2 CFR 200.500–200.517 

and as follows: 

(a) Grantees expending $750,000 or 

more Federal funds per fiscal year will 

submit an Audit conducted in 

accordance with 2 CFR parts 200, 215, 

220, 225, 230 and 400, ‘‘Uniform 

Administrative Requirements, Cost 

Principles, and Audit Requirements for 

Federal Awards.’’ 

(b) Grantees expending less than 

$750,000 will provide annual financial 

Statements covering the grant period, 

consisting of the organization’s 

statement of income and expense and 

balance sheet signed by an appropriate 

Official of the organization. Financial 

statements will be submitted within 90 

days after the Grantee’s fiscal year. 

§§ 3570.278—3570.280 [Reserved] 

§ 3570.281 Grant servicing. 

Grants will be serviced in accordance 

with 7 CFR part 1951, subpart E. 

§ 3570.282 [Reserved] 

§ 3570.283 Exception authority. 

The Administrator may make an 

exception to any requirement or 

provision of this subpart, if such an 

exception is necessary to implement the 

intent of the authorizing statutes in a 

time of national emergency or in 

accordance with a Presidentiallydeclared disaster, or on a case-by-case 

basis, when such an exception is in the 

best financial interest of the Federal 

Government and is otherwise not in 

conflict with applicable laws. No 

exceptions, however, will be granted for 

Applicant, Ultimate Recipient, or 

Project eligibility. 

§ 3570.284 Review or appeal rights. 

A person may seek a review of an 

Agency decision under this subpart 

from the appropriate Agency official 

that oversees the program in question or 

appeal to the USDA National Appeals 

Division in accordance with 7 CFR part 

11. 

§§ 3570.285–3570.299 [Reserved] 

§ 3570.300 OMB control number. 

The reporting and recordkeeping 

requirements contained in this 

regulation have been submitted to the 

Office of Management and Budget 

(OMB) for approval. 

Dated: December 11, 2015. 

Tony Hernandez, 

Administrator, Rural Housing Service. 

[FR Doc. 2016–00479 Filed 1–13–16; 8:45 am] 

BILLING CODE 3410–XV–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1275; Directorate 

Identifier 2014–NM–070–AD; Amendment 

39–18354; AD 2015–26–06] 

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) 2004–14– 

09 for certain Airbus Model A320–211, 

–212, and –231 airplanes. AD 2004–14– 

09 required repetitive inspections for 

fatigue cracking of the lower surface 

panel on the wing center box, and repair 

if necessary; and modification of the 

lower surface panel on the wing center 

box, which constitutes terminating 

action for the repetitive inspections. 

This new AD retains the requirements of 

AD 2004–14–09, reduces the 

compliance times for the repetitive 

inspections, and requires an additional 

repair for certain airplanes. This AD was 

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Federal Register / Vol. 81, No. 9 / Thursday, January 14, 2016 / Rules and Regulations 1871 

prompted by a determination that, based 

on the average flight duration, the 

average weight of fuel at landing is 

higher than that defined for the analysis 

of the fatigue-related tasks; and that shot 

peening might have been improperly 

done on the chromic acid anodizing 

(CAA) protection, which would 

adversely affect fatigue crack protection. 

We are issuing this AD to detect and 

correct fatigue cracking of the lower 

surface panel on the wing center box, 

which could result in reduced structural 

integrity of the airplane. 

DATES: This AD becomes effective 

February 18, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 18, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 13, 2004 (69 FR 

41398, July 9, 2004). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 27, 1998 (63 FR 

56542, October 22, 1998). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2015-1275; 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, 

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– 

1275. 

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 to supersede AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, 

July 9, 2004). AD 2004–14–09 applied to 

certain Airbus Model A320–211, –212, 

and –231 airplanes. The NPRM 

published in the Federal Register on 

May 8, 2015 (80 FR 26492). The NPRM 

was prompted by a determination that, 

based on the average flight duration, the 

average weight of fuel at landing is 

higher than that defined for the analysis 

of the fatigue-related tasks; and that shot 

peening might have been improperly 

done on the CAA protection, which 

would adversely affect fatigue crack 

protection. The NPRM proposed to 

continue to require repetitive 

inspections for fatigue cracking of the 

lower surface panel on the wing center 

box, and repair if necessary; and 

modification of the lower surface panel 

on the wing center box, which 

constitutes terminating action for the 

repetitive inspections. The NPRM also 

proposed to reduce the compliance 

times for the repetitive inspections, and 

would require a repair for certain 

airplanes. We are issuing this AD to 

detect and correct fatigue cracking of the 

lower surface panel on the wing center 

box, which could result in reduced 

structural integrity of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0065, dated March 14, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on certain Model 

A320–211, -212, and -231 airplanes. The 

MCAI states: 

During center fuselage certification full 

scale test, damage was found in the center 

wing box (CWB) lower surface panel. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the CWB. 

To prevent such damage, Airbus developed 

mod 22418 which consists in shot-peening of 

the lower panel in the related area. Mod 

22418 has been embodied in production from 

aeroplane [manufacturer serial number] 

(MSN) 0359. For unmodified in-service 

aeroplanes, Airbus issued Service Bulletin 

(SB) A320–57–1082 to introduce repetitive 

High Frequency Eddy Current (HFEC) 

inspections on the external face of the center 

wing box lower panel between Frame (FR) 41 

and FR42 to detect damage. 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD 2002–342 [http://

ad.easa.europa.eu/blob/20023420tb_

superseded.pdf/AD_F-2002-342_1] to require 

these inspections and, depending on 

findings, applicable corrective action(s). 

Airbus also issued SB A320–57–1043 as an 

optional terminating action for the repetitive 

inspections required by DGAC France AD 

2002–342. 

Since that [DGAC] AD was issued, the 

results of a survey, carried out on the A320 

fleet, highlighted some differences between 

the mission parameters, mainly on the weight 

of fuel at landing and on the average flight 

duration, which are higher than those 

defined for the analysis of the fatigue related 

tasks. 

These findings have led to an adjustment 

of the A320 reference fatigue mission. 

Consequently, the threshold and intervals of 

these repetitive inspections have been 

revised and a new threshold figure expressed 

in flight hours (FH) has been established. 

In addition, it has been identified that, on 

aeroplanes that have been modified in 

accordance with Airbus SB A320–57–1043 

(Airbus mod 22418) at Revision 05 or an 

earlier Revision, the shot peening may have 

been improperly done on the Chromic Acid 

Anodizing (CAA) protection, which has no 

fatigue benefit effect. Therefore, the 

inspections per Airbus SB A320–57–1082 are 

required again on these aeroplanes. 

Consequently, new shot-peening 

procedures with proper CAA protection 

removal instructions have been developed 

and their embodiment through Airbus SB 

A320–57–1043 Revision 06 cancels the 

repetitive inspections per Airbus SB A320– 

57–1082, as required by DGAC France AD 

2002–342. 

For the reasons described above, this new 

[EASA] AD retains the requirements of DGAC 

France AD 2002–342, which is superseded, 

but requires these actions to be accomplished 

within reduced thresholds and intervals. In 

addition, the optional terminating action 

provision (SB A320–57–1043) is amended by 

including reference to the SB at Revision 06. 

The optional terminating action 

described in Airbus Service Bulletin 

A320–57–1043, Revision 06, dated 

December 5, 2013, is accomplishing 

shot peening in the radius of the milling 

step between stiffeners 13 and 14 near 

the fuel pump aperture. You may 

examine the MCAI in the AD docket on 

the Internet at http://www.regulations.

gov/#!documentDetail;D=FAA-2015- 

1275-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 26492, May 8, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available 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 

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1872 Federal Register / Vol. 81, No. 9 / Thursday, January 14, 2016 / Rules and Regulations 

26492, May 8, 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 26492, 

May 8, 2015). 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–57–1043, Revision 06, dated 

December 5, 2013. This service 

information describes procedures for 

shot peening in the radius of the milling 

step between stiffeners 13 and 14 near 

the fuel pump aperture. 

Airbus has also issued Service 

Bulletin A320–57–1082, Revision 04, 

dated December 5, 2013. This service 

information describes procedures for 

inspections for cracking of the lower 

surface panel on the wing center box. 

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 46 

airplanes of U.S. registry. 

The actions that were required by AD 

2004–14–09, Amendment 39–13718 (69 

FR 41398, July 9, 2004), and retained in 

this AD take about 25 work-hours per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the actions that 

were required by AD 2004–14–09 is 

$2,125 per product. 

The new requirements of this AD will 

add no additional economic burden. 

We have received no definitive data 

that will enable us to provide cost 

estimates for the on-condition 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov/#!docketDetail;D=FAA-2015-1275; 

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 Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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 

removing Airworthiness Directive (AD) 

2004–14–09, Amendment 39–13718 (69 

FR 41398, July 9, 2004), and adding the 

following new AD: 

2015–26–06 Airbus: Amendment 39–18354. 

Docket No. FAA–2015–1275; Directorate 

Identifier 2014–NM–070–AD. 

(a) Effective Date 

This AD becomes effective February 18, 

2016. 

(b) Affected ADs 

This AD replaces AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004). 

(c) Applicability 

This AD applies to Airbus Model A320– 

211, –212, and –231 airplanes, certificated in 

any category, all manufacturer serial 

numbers, except those on which Airbus 

Modification 22418 has been embodied in 

production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a determination 

that, based on the average flight duration, the 

average weight of fuel at landing is higher 

than that defined for the analysis of the 

fatigue-related tasks; and that shot peening 

might have been improperly done on the 

chromic acid anodizing (CAA) protection, 

which would adversely affect fatigue crack 

protection. We are issuing this AD to detect 

and correct fatigue cracking of the lower 

surface panel on the wing center box (WCB), 

which could result in reduced structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections, With No 

Changes 

This paragraph restates the requirements of 

paragraph (a) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with no changes. Except as provided 

by paragraph (k) of this AD: Prior to the 

accumulation of 20,000 total flight cycles, or 

within 60 days after November 27, 1998 (the 

effective date of AD 98–22–05, Amendment 

39–10851 (63 FR 56542, October 22, 1998)), 

whichever occurs later, perform a high 

frequency eddy current (HFEC) inspection to 

detect fatigue cracking of the lower surface 

panel on the WCB, in accordance with 

Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997; or 

Revision 03, dated April 30, 2002. Repeat the 

HFEC inspection thereafter at intervals not to 

exceed 7,500 flight cycles until the actions 

required by paragraph (i) of this AD are 

accomplished. 

(h) Retained Repair, With No Changes 

This paragraph restates the requirements of 

paragraph (b) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with no changes. Except as provided 

by paragraph (j) of this AD, if any cracking 

is detected during any inspection required by 

paragraph (g) of this AD: Prior to further 

flight, repair in accordance with Airbus 

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Federal Register / Vol. 81, No. 9 / Thursday, January 14, 2016 / Rules and Regulations 1873 

Service Bulletin A320–57–1082, Revision 01, 

dated December 10, 1997; or Revision 03, 

dated April 30, 2002. Accomplishment of the 

repair constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD for the repaired area only. 

(i) Retained Inspection/Modification/Repair, 

With New Terminating Action 

This paragraph restates the requirements of 

paragraph (c) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with new terminating action provided. 

Prior to the accumulation of 25,000 total 

flight cycles, or within 60 days after 

November 27, 1998 (the effective date of AD 

98–22–05, Amendment 39–10851 (63 FR 

56542, October 22, 1998)), whichever occurs 

later: Perform an HFEC inspection to detect 

fatigue cracking of the lower surface panel on 

the WCB, in accordance with Airbus Service 

Bulletin A320–57–1082, Revision 01, dated 

December 10, 1997; or Revision 03, dated 

April 30, 2002. Accomplishment of the initial 

inspection required by paragraph (p) of this 

AD constitutes terminating action for the 

inspection requirements of this paragraph. 

(1) If no cracking is detected: Prior to 

further flight, modify the lower surface panel 

on the WCB, in accordance with Airbus 

Service Bulletin A320–57–1043, Revision 02, 

dated May 14, 1997; or Revision 05, dated 

April 30, 2002. Accomplishment of the 

modification constitutes terminating action 

for the requirements of paragraph (g) of this 

AD. 

(2) Except as provided by paragraph (j) of 

this AD: If any cracking is detected, prior to 

further flight, repair in accordance with 

Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997, or 

Revision 03, dated April 30, 2002; and 

modify any uncracked area, in accordance 

with Airbus Service Bulletin A320–57–1043, 

Revision 02, dated May 14, 1997, or Revision 

05, dated April 30, 2002. Accomplishment of 

the repair of cracked area(s) and modification 

of uncracked area(s) constitutes terminating 

action for the requirements of paragraph (g) 

of this AD. 

(j) Retained Service Bulletin Exception, With 

Revised Repair Instructions 

This paragraph restates the requirements of 

paragraph (d) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with revised repair instructions. If any 

cracking is detected during any inspection 

required by paragraph (h) or (i)(2) of this AD, 

and the applicable service bulletin specifies 

to contact Airbus for an appropriate action: 

Prior to further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, FAA, Transport Airplane 

Directorate; or the Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) (or its delegated 

agent); or the European Aviation Safety 

Agency (EASA); or Airbus’s EASA Design 

Organization Approval (DOA). After the 

effective date of this AD only repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA; or 

Airbus’s EASA DOA. 

(k) Retained Provision for Certain Inspection 

Exception, With No Changes 

This paragraph restates the provision of 

paragraph (e) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with no changes. The actions required 

by paragraph (g) of this AD are not required 

to be accomplished if the requirements of 

paragraph (i) of this AD are accomplished at 

the time specified in paragraph (g) of this AD. 

(l) Retained Initial Inspection, With 

Terminating Action 

This paragraph restates the requirements of 

paragraph (f) of AD 2004–14–09, Amendment 

39–13718 (69 FR 41398, July 9, 2004), with 

terminating action provided. For airplanes on 

which neither the inspection required by 

paragraph (g) of this AD nor the modification 

required by paragraph (i)(1) of this AD has 

been done before August 13, 2004 (the 

effective date of AD 2004–14–09): Perform an 

HFEC inspection to detect fatigue cracking of 

the lower surface panel on the WCB, in 

accordance with Airbus Service Bulletin 

A320–57–1082, Revision 01, dated December 

10, 1997; or Revision 03, dated April 30, 

2002; at the later of the times specified in 

paragraphs (l)(1) and (l)(2) of this AD. 

Accomplishment of the inspection required 

by this paragraph terminates the 

requirements of paragraph (g) of this AD. 

Accomplishment of the initial inspection 

required by paragraph (p) of this AD 

terminates the inspection requirements of 

this paragraph. 

(1) Prior to the accumulation of 13,200 

total flight cycles or 39,700 total flight hours, 

whichever is first. 

(2) Prior to the accumulation of 20,000 

total flight cycles, or within 3,500 flight 

cycles after August 13, 2004 (the effective 

date of AD 2004–14–09, Amendment 39– 

13718 (69 FR 41398, July 9, 2004)), 

whichever is later. 

(m) Retained Repetitive Inspections, With 

No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with no changes. If no cracking is 

detected during the inspection required by 

paragraph (g) or (l) of this AD: Repeat the 

inspection required by paragraph (l) of this 

AD at the applicable time specified in 

paragraph (m)(1) or (m)(2) of this AD. 

Accomplishment of the modification 

required by paragraph (i)(1) of this AD 

terminates the requirements of this 

paragraph. 

(1) For airplanes on which the inspections 

required by paragraph (g) of this AD have 

been initiated before August 13, 2004 (the 

effective date of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004)): Do the next inspection within 5,700 

flight cycles after accomplishment of the last 

inspection, or within 1,800 flight cycles after 

August 13, 2004, whichever is later. Repeat 

the inspection thereafter at intervals not to 

exceed 5,700 flight cycles. 

(2) For airplanes on which no inspection 

required by paragraph (g) of this AD has been 

done before August 13, 2004 (the effective 

date of AD 2004–14–09, Amendment 39– 

13718 (69 FR 41398, July 9, 2004)): Do the 

next inspection within 5,700 flight cycles 

after accomplishment of the inspection 

required by paragraph (l) of this AD. Repeat 

the inspection thereafter at intervals not to 

exceed 5,700 flight cycles. 

(n) Retained Repair/Modification, With 

Revised Repair Instructions 

This paragraph restates the requirements of 

paragraph (h) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with revised repair instructions. If any 

cracking is detected during any inspection 

required by paragraph (l) or (m) of this AD, 

prior to further flight, repair in accordance 

with Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997, or 

Revision 03, dated April 30, 2002; and 

modify any uncracked area, in accordance 

with Airbus Service Bulletin A320–57–1043, 

Revision 02, dated May 14, 1997, or Revision 

05, dated April 30, 2002. Where Airbus 

Service Bulletin A320–57–1082 specifies to 

contact Airbus for an appropriate repair 

action: Prior to further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the DGAC 

(or its delegated agent)); or EASA; or Airbus’s 

EASA DOA. After the effective date of this 

AD only repair using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. 

Accomplishment of the repair of cracked 

area(s) and modification of uncracked area(s) 

constitutes terminating action for the 

requirements of paragraphs (g) through (n) of 

this AD. 

(o) New Requirement of This AD: Repair of 

Certain Airplanes 

For airplanes on which the actions 

specified in Airbus Service Bulletin A320– 

57–1043 have not been accomplished, and on 

which a repair has been accomplished, as 

specified in the service information 

identified in paragraph (o)(1), (o)(2), (o)(3), or 

(o)(4) of this AD: Within 30 days after the 

effective date of this AD, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; the EASA; or 

Airbus’s EASA DOA. 

(1) Airbus Service Bulletin A320–57–1082, 

dated October 31, 1996. 

(2) Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997. 

(3) Airbus Service Bulletin A320–57–1082, 

Revision 02, dated July 26, 1999. 

(4) Airbus Service Bulletin A320–57–1082, 

Revision 03, dated April 30, 2002. 

(p) New Requirement of This AD: Repetitive 

WCB Inspections 

At the applicable time specified in 

paragraphs (p)(1) and (p)(2) of this AD: Do an 

HFEC inspection for cracking of the lower 

surface panel on the WCB, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1082, 

Revision 04, dated December 5, 2013. Repeat 

the inspection of the lower surface panel on 

the WCB thereafter at intervals not to exceed 

7,200 flight cycles or 14,400 flight hours, 

whichever occurs first. Accomplishment of 

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the initial inspection required by this 

paragraph terminates the inspections 

required by paragraphs (g), (i), and (l) of this 

AD. 

(1) For airplanes on which the actions 

specified in Airbus Service Bulletin A320– 

57–1043 have not been done: At the later of 

the times specified in paragraphs (p)(1)(i) and 

(p)(1)(ii) of this AD. 

(i) Before the accumulation of 20,700 flight 

cycles or 41,400 flight hours, whichever 

occurs first since first flight of the airplane. 

(ii) Within 7,200 flight cycles or 14,400 

flight hours, whichever occurs first after 

doing the most recent inspection as specified 

in the service information specified in 

paragraph (o)(1), (o)(2), (o)(3), or (o)(4) of this 

AD. 

(2) For airplanes on which the actions 

specified in Airbus Service Bulletin A320– 

57–1043 have been done: At the latest of the 

times specified in paragraphs (p)(2)(i), 

(p)(2)(ii), and (p)(2)(iii) of this AD. 

(i) Within 7,200 flight cycles or 14,400 

flight hours, whichever occurs first since 

doing the actions specified in Airbus Service 

Bulletin A320–57–1043. 

(ii) Within 3,750 flight cycles or 7,500 

flight hours, whichever occurs first after July 

31, 2012 (as described in Airbus Service 

Bulletin A320–57–1082, Revision 04, dated 

December 5, 2013). 

(iii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first after the 

effective date of this AD. 

(q) New Requirement of This AD: Repair of 

WCB 

If any crack is found during any inspection 

required by paragraph (p) of this AD: Before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; the EASA; or Airbus’s 

EASA DOA. 

(r) New Optional Terminating Action 

Modification of an airplane, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1043, 

Revision 06, dated December 5, 2013, 

constitutes terminating action for the actions 

required by paragraph (p) of this AD. 

(s) Credit for Previous Actions 

This paragraph provides credit for 

applicable actions required by paragraphs (g) 

through (n) of this AD, if those actions were 

performed before the effective date of this AD 

using the applicable Airbus Service 

Information provided in paragraphs (s)(1) 

through (s)(8) of this AD. 

(1) Airbus Service Bulletin A320–57–1043, 

dated February 16, 1993, which is not 

incorporated by reference in this AD. 

(2) Airbus Service Bulletin A320–57–1043, 

Revision 01, dated June 14, 1996, which is 

not incorporated by reference in this AD. 

(3) Airbus Service Bulletin A320–57–1043, 

Revision 02, dated May 14, 1997, which was 

incorporated by reference on November 27, 

1998 (63 FR 56542, October 22, 1998). 

(4) Airbus Service Bulletin A320–57–1043, 

Revision 03, dated October 24, 1997, which 

is not incorporated by reference in this AD. 

(5) Airbus Service Bulletin A320–57–1043, 

Revision 04, dated May 15, 1999, which is 

not incorporated by reference in this AD. 

(6) Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997, which 

was incorporated by reference on November 

27, 1998 (63 FR 56542, October 22, 1998). 

(7) Airbus Service Bulletin A320–57–1082, 

Revision 02, dated July 26, 1999, which is 

not incorporated by reference in this AD. 

(8) Airbus Service Bulletin A320–57–1082, 

Revision 03, dated April 30, 2002, which was 

incorporated by reference on August 13, 2004 

(69 FR 41398, July 9, 2004). 

(t) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, 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. 

(u) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0065, dated 

March 14, 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– 

2015–1275. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (v)(6) and (v)(7) of this AD. 

(v) 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. 

(3) The following service information was 

approved for IBR on February 18, 2016. 

(i) Airbus Service Bulletin A320–57–1043, 

Revision 06, dated December 5, 2013. 

(ii) Airbus Service Bulletin A320–57–1082, 

Revision 04, dated December 5, 2013. (4) The 

following service information was approved 

for IBR on August 13, 2004 (69 FR 41398, 

July 9, 2004). 

(i) Airbus Service Bulletin A320–57–1043, 

Revision 05, dated April 30, 2002. 

(ii) Airbus Service Bulletin A320–57–1082, 

Revision 03, dated April 30, 2002. 

(5) The following service information was 

approved for IBR on November 27, 1998 (63 

FR 56542, October 22, 1998). 

(i) Airbus Service Bulletin A320–57–1043, 

Revision 02, dated May 14, 1997. Pages 1 

through 6, 8, 13, and 14 of this service 

bulletin are marked Revision 02, dated May 

14, 1997; pages 7, 9 through 12, and 15 of 

this service bulletin are from the original 

issue, dated February 16, 1993. 

(ii) Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997. 

(6) 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. 

(7) 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. 

(8) 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/ibr-locations.html. 

Issued in Renton, Washington, on 

December 18, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–32519 Filed 1–13–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1982; Directorate 

Identifier 2014–NM–108–AD; Amendment 

39–18353; AD 2015–26–05] 

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 all 

Fokker Services B.V. Model F.28 Mark 

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